Tab 04 SOW Additional Documents Referenced in SOW.pdf

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FRCSE TECHNICAL

DIRECTIVE COVER SHEET

RELEASED FOR

COMPLIANCE

If printed from Intra1 and retained, contact CTPL @ 790-4838 or 790-5010 for processing instructions to satisfy requirements in NA 00-

25-100, WP 013-00, paragraph 12-2.

U

NITED STATES OF AMERIC

A

D E

PA

RTMENT OF DEFE

N S

DEPARTMENT OF THE NAVY

NAVAL AIR SYSTEMS COMMAND

RADM WILLIAM MOFFETT BUILDING

47123 BUSE RD, BLDG 2272

PATUXENT RIVER, MARYLAND 20670-1547

IN REPLY REFER TO:

Code: 43320

LES/JX T34-0020

Date: 7 January 2013

TITLE: T-34 Local Engineering Specification

SUBJECT: Nose Landing Gear Fork Assy 200/400 hr Inspection & Identification

IDENTIFICATION: LES/JX T34-0020

SYSTEM: Landing Gear

WORK UNIT CODE: N/A

CLASSIFICATION: Conditional.

Conditions requiring inspection of the Nose Landing Gear (NLG) Fork are:

NLG Fork Assemblies having 8000-12000 landings: Inspect per this LES every 400 flight hours.

NLG Fork Assemblies having over 12,000 landings: Inspect per this LES every 200 flight hours.

NLG Fork Assemblies having less than 8000 landings do not require non-destructive inspection (NDI) per this LES.

REFERENCES:

(a) Hawker Beechcraft Corporation No. 92-37867. “T-34C Maintenance Manual”

(b) T-34C Accessory Bulletin No. 1177, NLG Fork Assemblies Inspection (inactive).

(c) LPS 250, “Removal of Organic Coatings from Aircraft & Components.”

(d) LPS 1520, “Fluorescent Penetrant Inspection.”

(e) LPS 1590, “Special Cleaning Procedures for Use of the Vapor Degreaser.”

(f) A-A-208, “Ink, Marking, Stencil, Opaque (Porous and Non-Porous Surfaces).”

ENCLOSURES: None

1. PURPOSE: To provide the inspection and identification requirements for existing and new T-34C NLG fork assemblies, p/n: 104-820041-1.

2. CANCELLATION: N/A

3. BACKGROUND: T-34 NLG fork assemblies require repetitive non-destructive inspections to inspect for the presence of cracks. Inspection requirements originated in reference (a) and were further refined in reference (b). In addition to providing inspection requirements, reference (b) required serialization of the NLG forks for tracking. This serializing was performed using the vibropeen technique, which etches into the steel NLG fork assembly. Recent inspections of the NLG fork assemblies during landing gear overhaul found engraved identification numbers did

7 January 2013 not always conform to accepted standard vibropeening practice. This LES will provide complete instructions for performing the required 200 hr and 400 hr inspections that encompass the original intent of reference (a) and reference (b), and adds inspection requirements for area surrounding vibropeened serial numbers. The scope of the 200 and 400 hr inspections is identical. In addition to inspection requirements, this LES will provide new instructions for marking the serial number of the NLG Fork assemblies, eliminating the requirement for vibropeening.

4. APPLICATION: T-34C

5. SPECIAL FACILITIES REQUIRED: None

6. SPECIAL CERTIFICATION, TRAINING, OR SKILLS REQUIRED: None

7. SPECIAL TOOLS AND TEST EQUIPMENT: None

8. SPECIAL MATERIALS: Decal, P/N: JX34DD00105

9. EFFECTIVE DATE: As indicated on the Fleet Readiness Centers Southeast (FRCSE) Technical Data Cover Sheet, FRCSE 5070/13, as affixed.

10. INSTRUCTIONS:

NOTE

Inspection and Identification of the NLG Fork Assemblies by facilities other than FRCSE are not required to use the identical FRCSE Local Process Specifications (LPSs) or Decals called out in this LES. This LES may be performed using the facilities own LPSs and Decals providing they meet the intent of the LPSs and instructions referenced in this LES. Contact FST Engineering for copies of FRCSE LPSs.

Non-Destructive Inspection

Cadmium plating shall NOT be removed from the NLG axle. Only the paint shall be stripped from the NLG Fork Assy for inspection.

10.1. Strip entire NLG Fork Assy of paint using Plastic Media Blast (PMB) Type V per reference (c).

10.2. Fluorescent Penetrant Inspect the entire NLG Fork per reference (d), using Type 1, Method D, Level IV Penetrant and Form A developer. Fluorescent Penetrant Inspection of the plated axle and strut is not required.

10.2.1. Pay particular attention to welded joints and the area surrounding and

1.0 inch beyond the vibropeened serial numbers in the Fork.

10.2.2. No cracks indications permitted. Cracks are cause for rejection of the part.

It is imperative FST Engineering is notified if a crack is confirmed in the NLG Fork.

10.2.2.1. Any NLG Fork with a confirmed crack shall be reported to FST Engineering, then scrapped.

10.3. Vapor Degrease NLG Fork Assembly per reference (e).

10.4. Prime NLG Fork Assembly with MIL-PRF-85582, Class C, Type 1.

10.5. Topcoat NLG Fork Assembly with MIL-PRF-85285, Type IV, Color Code 17925 (Gloss White).

Identification

CAUTION

Do NOT remove any existing engraved serial numbers on NLG Fork Assy. Do NOT vibropeen or otherwise etch into the NLG Fork Assy.

Serial and part number shall be included on the computer-generated decal P/N JX34DD00105 at Depot sites. Contractor sites that receive blank decals may print the serial number onto the decal with ink conforming to reference (f).

10.6. Identify NLG Fork Assy Part Number and Serial Number using Decal

JX34DD00105.

During original serialization, NLG Fork Assy serial numbers began with an “FA” followed by the digits of the serial number of the landing gear assembly in which that fork was installed. (Example: If NLG Assy S/N was 123, NLG Fork Assy S/N FA-123 was assigned). Some serial numbers included the location of serialization between the “FA” and number (i.e. FA-WF-123 would be a NLG Fork Assy that was serialized at Whiting

Field).

Existing NLG Fork Assembly serial numbers will NOT be changed, regardless of which NLG

Assembly they are installed in. Factory new NLG Forks will be serialized based on a new numbering system per this LES.

10.6.1. NLG Fork Serial number identified on the JX34DD00105 Decal shall match the serial number on the existing NLG Fork Assy EHR card.

Existing NLG Fork Assy serial numbers are NOT dependent on installation or any other serial number.

10.6.2. Factory New NLG Fork Assemblies shall be identified with serial numbers provided by FST Engineering. New serial numbers generated for factory new NLG Forks will be formatted in the following manner:

10.6.2.1. New NLG Fork Assemblies installed at FRCSE shall begin with “FA-” followed by “FRCSE”, followed by the digits of the serial number (Example, the first new NLG Fork Assy installed at FRCSE will be serialized FA-FRCSE-1).

10.6.2.2. New NLG Fork Assemblies installed at FRCSW shall begin with “FA-” followed by “FRCSW”, followed by the digits of the serial number (Example, the first new NLG Fork Assy installed at FRCSW will be serialized FA-FRCSW-1).

10.6.2.3. New NLG Fork Assemblies installed at NAS Corpus Christi shall begin with “FA-” followed by “CC”, followed by the digits of the serial number (Example, the first new NLG Fork Assy installed at NAS Corpus Christi will be serialized FA-CC-1).

10.6.2.4. New NLG Fork Assemblies installed at NAS Whiting Field shall begin with “FA-” followed by “WF”, followed by the digits of the serial number (Example, the first new NLG Fork Assy installed at NAS Whiting Field will be serialized FA-WF-1).

10.6.3. Wipe NLG fork arm free of grease and dirt using isopropyl alcohol, or equivalent, to prepare NLG fork arm for decal application.

Do NOT install decal over previously engraved numbers. Installing decal over engraved numbers can trap moisture and lead to corrosion.

10.6.4. Apply self-adhesive Decal JX34DD00105 on the NLG fork arm as depicted in Figure 1. Do NOT install decal over previously engraved numbers.

10.6.5. Seal the decal by applying gloss clear polyurethane edge sealer qualified to MIL-PRF-85285, Type I (NSN: 8010-01-356-5171, or equivalent) over and around the decal. Sealer shall overlap decal 0.2-inch and extend over fork beyond decal edges 0.5-inch (minimum).

Allow sealer to cure IAW manufacturer’s instructions

Figure 1: Installation location of JX34DD00105 Decal on NLG Fork Assy

11. LOGBOOK ENTRY:

11.1. For existing NLG Fork Assemblies:

11.1.1. Update NLG Fork Assy EHR card to reflect completion of the 200/400 hr inspection.

11.2. For New NLG Fork Assemblies:

11.2.1. Create new NLG Fork Assy EHR card, utilizing serial number provided by FST Engineering.

12. SIGNATURES:

PREPARED BY:

David Pfeffer/Code 4.3.3.2 Team Lead CNATRA FST (Primary/Multi-Engine Aircraft)

REVIEWED BY:

Michael List/Code 4.3.3.2 Structures Engineer

APPROVED BY:

David Stricklin/Code 4.3.4 Division Director Materials Engineering Division

RELEASED BY:

Hector Perez/Code 4.1.1.2 CNATRA FST Lead By Direction of the Assistant Commander for Research and Engineering

Text1: C/W :

2ZQ00B, 2PD00B, 2PD000, 2PN00P, 2PC00B

Text2: 10 JAN 2013

T-34 LES T34-0020

25-100, WP 013-01, paragraph 13-4b.

UNITED STATES OF AMERIC

RTMENT OF DEFEN

SE

LES/JX T-34 0022

Date: 19 Dec 16

SUBJECT: T-34 Front Spar Carry-Thru Reinforcement Strap Repair

IDENTIFICATION: LES/JX T-34 0022

SYSTEM: Airframe

WORK UNIT CODE: 11T52V0

CLASSIFICATION: Conditional. For T-34C aircraft found with damage to the Reinforcement Strap, P/N 104-430057-1, and/or the L/H and/or R/H Main Landing Gear Retract Rod, P/N (70898) 35-815125-49/-51, during ACI.

REFERENCES: (a) Raytheon Aircraft Doc. 92-37867 T-34C Maintenance Manual

(b) Raytheon Aircraft Doc. 92-37869C Illustrated Parts Catalog for

T-34C

(c) LPS/JX 320 Chemical Conversion Coatings on Aluminum and

Aluminum Alloys

(d) LPS/JX 650 Application of Organic Coatings to Aircraft

(e) NAVAIR 01-1A-8 Structural Hardware

(f) LPS/JX 1210 Manual and Portable Machine Hole Manufacturing

(g) LPS/JX 1500 Ultrasonic Inspection Local Processing

Specification

ENCLOSURES: (1) JX34TA00104-1 Tool Usage Instructions

1. PURPOSE: To provide instructions for inspecting, repairing, and replacing the P/N 104-430057-1 Reinforcement Strap and to provide instructions for inspecting and replacing the P/N 35-815125-49/-51 Retract Rod Assembly.

2. CANCELLATION: None

3. BACKGROUND: During Aircraft Condition Inspection (ACI), the Reinforcement Strap, P/N (70898) 104-430057-1 (referred to as “Bow Tie Doubler”), installed on the Forward Carry Thru (FCT) Assembly, P/N (70898) 104-410013-1, has exhibited significant wear in service due to deflections and/or permanent deformation of the Left Hand (L/H) Main Landing Gear (MLG) Retract Rod Assembly, P/N 35-815125-49 (referred to as “White Rod”), which makes contact with the FCT Assembly Bow Tie Doubler during landing gear operation. JX34TA00104-1 Inspection Tool Assembly was developed to inspect the Retract Rod Assembly.

This instruction was developed to provide depot maintenance procedures for the

19 Dec 16 T-34C Main Landing Gear (MLG) Retract Rod installation and function check, and for the repair or replacement of the Bow Tie Doubler, as required.

6. SPECIAL CERTIFICATION, TRAINING, OR SKILLS REQUIRED:

FRC Certified Level II NDI Inspector (per FRCSEINST 4855.2)

7. SPECIAL TOOLS AND TEST EQUIPMENT:

JX34TA00104-1 Inspection Tool Assembly for P/N 35-815125-49

Aluminum Step Wedge 7075-T6, SN 50034, 0.020 – 0.100 inch

8. SPECIAL MATERIALS: None

9. EFFECTIVE DATE: As indicated on the Fleet Readiness Center Southeast (FRCSE) Technical Data Cover Sheet as affixed.

10.1. Inspection of Main Landing Gear (MLG) Retract Rod (“White Rod”):

10.1.1. Remove the L/H and R/H MLG White Rods, P/N (70898)

35-815125-49/-51, in accordance with (IAW) reference (a), Chapter 32-10-00, Main Gear Removal.

10.1.2. Inspect the Retract Rods utilizing the JX34TA00104-1 tool assembly per instructions in Enclosure (1).

10.1.2.1. If necessary, procure a new MLG White Rod. Verify new White Rod is acceptable utilizing the JX34TA00104-1 tool assembly per instructions in Enclosure (1).

10.2. Inspection of Forward Carry Thru (FCT) Assembly Bow Tie Doubler:

10.2.1. Visually inspect Bow Tie Doubler for gouges, corrosion, or other defects. The typical damaged area of the Bow Tie Doubler is shown in Figures 1 and 2.

10.2.1.1. Measure damaged area. If damage does not exceed 0.025 inch deep, 0.50 inch long, and 0.25 inch wide, blend damage as instructed in Step 10.4. If damage does exceed the specified limits, replace doubler as instructed in Step 10.5.

10.3. Inspection of Forward Carry Thru (FCT) Assembly Spar Web:

10.3.1. Visually inspect the spar web, P/N 104-430023-3, for gouges, creases or other defects in the vicinity of the Bow Tie Doubler (Figures 2 and 3).

10.3.2. If necessary, remove surface damage by blending the web in the area shown in Figure 2 IAW Step 10.6.

10.3.3. If necessary, hand form the spar web at creased area to within +/-0.010 inch of B/P profile. Take care not to damage any surrounding and/or underlying structure. It is acceptable to remove Bow Tie Doubler, P/N 104-430057-1, and support angle, P/N 104-430056-1, to facilitate forming.

Figure 1. Typical Damaged Area

(Excerpts from Reference (b), Chapters 32 and 53)

Figure 2. Typical Damage Looking Forward at FCT Web Assembly

Figure 3. Creased/Dented FCT Web Assembly

10.4. Blending Bow Tie Doubler Damage

10.4.1. Blend the damage of the Bow Tie Doubler, blend only what is required to remove evidence of the damage. Maintain blend ratio of 5:1, min 125 Ra/RHR or smoother surface finish. Maintain a minimum 2D edge distance on all fasteners.

10.4.2. Measure blended area. If blend exceeds 0.025 inch deep, 0.50 inch long, and 0.25 inch wide (refer to Figure 4), continue to Step 10.5.

10.4.3. Chemical conversion coat all bare metal using MIL-DTL-81706, Type I, Class 1A IAW reference (c) or reference (d) and prime using MIL-PRF-23377, Type I, Class C2, IAW reference (d).

10.4.4. Install the MLG Retract Rod IAW reference (a), Chapter 32-30-00, Landing Gear and Actuator Installation and the MLG IAW Chapter 32-10-00 Main Gear Installation.

10.4.5. Cycle the MLG to verify a minimum clearance of 0.030 inch between the LH rod (P/N 35-815125-49) and Bow Tie Doubler.

10.4.5.1. If minimum clearance does exist, repair is acceptable. No further work required. Continue processing the aircraft per ACI requirements.

10.4.5.2. If minimum clearance does not exist, proceed as follows:

10.4.5.2.1. Further blend the Bow Tie Doubler at the area of minimum clearance; maximum blend dimensions shall not exceed

0.50 inch long, 0.25 inch wide, and 0.025 inch deep (Figure 4).

Figure 4. Maximum Bow Tie Doubler Blend Dimensions (in inches)

10.4.5.2.2. Chemical conversion coat all bare metal using

MIL-DTL-81706, Type I, Class 1A IAW reference (c) or reference (d) and prime using MIL-PRF-23377, Type I, Class C2, IAW reference (d).

10.4.5.2.3. Repeat Step 10.4.5. If minimum clearance does not exist, contact CNATRA FST Engineering.

10.5. Replacement of Bow Tie Doubler

10.5.1. Remove the existing Bow Tie Doubler and existing support angle, P/N (70898) 104-430056-1, installed on the forward side of the FCT aft web by carefully removing 13 rivets attaching the doubler to the aft web of the FCT assembly. Remove fasteners IAW reference (e). Retain the doubler and support angle.

10.5.1.1. Use care not to damage the FCT web/assembly.

10.5.1.2. Verify the existing fastener holes common to the doubler in the FCT aft web are in compliance with the hole requirements of references (e) and (f).

10.5.1.2.1. Holes shall be clean, straight, and round to within 0.002 inch.

10.5.1.2.2. Contact CNATRA FST Engineering if holes do not meet the above requirements.

10.5.2. Fabricate new doubler from 0.050 inch thick 2024-T3 clad aluminum sheet (AMS QQ-A-250/5) per the sample doubler removed in Step

10.5.1 and as shown in Figure 5.

10.5.2.1. Fabricate without holes except the 0.096/0.101 inch pilot specified in Figure 5.

10.5.2.2. Deburr all sharp edges.

10.5.2.3. Chemical conversion coat all bare metal using MIL-DTL-81706, Type I, Class 1A IAW reference (c) or reference (d) and prime using MIL-PRF-23377, Type I, Class C2, IAW reference (d).

10.5.2.4. Identify Doubler as "WC3LESJXT340022-001" in 0.13 inch high letters using indelible ink.

10.5.3. Install -001 Bow Tie Doubler and support angle, P/N (70898) 104-430056-1, using fasteners shown in Figure 6. Match drill existing fastener locations in FCT assembly as required. Determine fastener grip length at installation. Install fasteners per reference (e).

10.5.3.1. Chemical conversion coat all bare metal using MIL-DTL-81706, Type I, Class 1A IAW reference (c) or reference (d) and prime using MIL-PRF-23377, Type I, Class C2, IAW reference (d).

Figure 5. Dimensions of Bow Tie Doubler (in inches)

Figure 6. Replacement Bow Tie Doubler Installation (in inches)

Perform Step 10.6 if blending of the

P/N 104-430023-3 Spar Web is required per Step 10.3. Otherwise, proceed to Step 10.7.

10.6. Blending of Spar Web

10.6.1. Remove fasteners as required to gain access for rework IAW reference (e). Remove and retain the Bow Tie Doubler and support angle, P/N 104-430056-1.

10.6.2. If required, mask off other areas or temporarily block with stainless steel shims to protect surrounding structure from damage during the damage removal operation.

10.6.3. Use a maximum 180-220 grit paper or tool and an approximate

0.25 inch minimum blend radius to blend out/remove the damage.

10.6.4. Do not blend partially across fastener location. If blending is required near fasteners (within 0.10 inch), blend across such fasteners and capture the entire fastener.

10.6.5. Do not remove more material than required to remove the damage.

Maximum blend depth shall not exceed 0.004 inch and minimum section thickness shall not be less than 0.036 inch.

10.6.6. If the above rework limitations cannot be maintained, discontinue rework at the maximum allowed limitation and submit condition with estimate of remaining depth or rework required to eliminate the damage to CNATRA FST engineering.

10.6.7. The rework area shall present as a smooth and gradual transition between the reworked and non-reworked areas with an approximate 20:1 width to depth ratio.

10.6.8. Chemical conversion coat all bare metal using MIL-DTL-81706, Type I, Class 1A IAW reference (c) or reference (d).

10.6.9. Verify the nominal and the remaining thicknesses using ultrasonic inspection IAW reference (g). Minimum remaining thickness shall be

0.036 inch or greater.

10.6.9.1. Use aluminum step wedge 7075-T6, SN 50034, 0.020 – 0.100 inch or equivalent. Standardize using step thicknesses of 0.020 inch for the thin step and 0.100 inch for the thick step.

10.6.9.2. Contact CNATRA FST engineering if any additional discrepancies are found.

10.6.10. Prime all bare metal using MIL-PRF-23377, Type I, Class C2 IAW reference (d).

10.6.11. Inspect removed Bow Tie Doubler IAW Step 10.2. If required, perform repair IAW Step 10.4 or replacement IAW Step 10.5. Otherwise, reinstall Bow Tie Doubler and support angle using fasteners as shown in Figure 6. Install fasteners per reference (e).

10.7. Install the MLG Retract Rod IAW reference (a), Chapter 32-30-00 Landing Gear and Actuator Installation and the MLG IAW Chapter 32-10-00 Main Gear Installation.

10.8. During functional check of MLG, verify minimum gap of 0.030 inch exists between the LH Retract Rod and the Bow Tie Doubler. If the minimum gap does not exist, blend Bow Tie Doubler IAW step 10.4.

11. LOGBOOK ENTRY: Annotate the following in the miscellaneous history section of the subject aircraft logbook: “[Part Nomenclature] was [repaired or replaced] IAW FRCSE LES/JX T-34 0022 on [date].”

Veronica Aiu/Code 4.3.3.2

REVIEWED BY:

Rosa Cafasso/Code 4.3.3.2

Justin Hirt/Code 4.3.3.2 Structures Team Lead

David Brock/Code 4.3.4 Materials Engineering Division Director

David Pfeffer/Code 4.1.1.1

By Direction of the Assistant Commander for Research and Engineering

13. DISTRIBUTION: Code 4.3.3.2 Code 6.2.3.7 Code 6.2.7.0 Code 6.2.9.0

Rosa Cafasso/C/Code 4

Juuuuuuuuuuustststsssststtstiniiiiii Hirt/Code 4.3 StStStStStStStSStSSSSS ructures Team Le

David Pfeffer/CoCCCCCCCCCCCCCCCCCCCCCC dededdddddedededdeddededdddedddddddddddd 4 1 1

JX34TA00104-1 TOOL USAGE INSTRUCTIONS

LES/JX T-34 0022 Enclosure (1)

1. Insert Pin, P/N JX34TA00104-9 (Alt: AN6-21A bolt), into the bushed holes of JX34TA00104-1 inspection tool and Heim bearing common to the main landing gear retract rod (“White Rod”), P/N 35-815125-37/-39/-49/-51, as shown in Figure 1.

Figure 1. Pinned White Rod

2. Rotate inspection tool until tool contacts white-rod as shown in Figure 2. Ensure dog-leg/fitting nests in inspection tool’s cutout.

Figure 2. Installed Inspection Tool

Point A

Point B

MLG Retract Rod (“White Rod”), P/N 35-815125-37/-39-/-49/-51

Inspection Tool, P/N JX34TA00104-1

Pin, P/N JX34TA00104-9

Pin, P/N JX34TA00104-7

For the L/H White Rod, any gap at Point A will indicate that the L/H White Rod is moved forward, closer to the forward carry-thru (FCT) web. For the R/H White Rod, any gap at

Point A will indicate the R/H White Rod is moved aft, closer to the floor support column.

3. Inspect for a gap at Point A, as shown in Figure 3. Insert feeler gauge between the White Rod tube and the inspection tool.

a. Any gap in excess of 0.021-inch is indicative of the Heim bearing being offset greater than 0.030-inch from the White Rod tube’s centerline and is cause for rejection and replacement of the White Rod.

Figure 3. Inspection of gap at Point A

4. Inspect for gap at Point B, as shown in Figure 4.

a. If a gap is noted at Point B, proceed as follows:

The dog-leg/fitting will not nest in the tool’s cutout for this inspection.

i. Remove the pin (-9) from the tool’s bushed holes and twist the White Rod 180°.

ii. Re-insert the pin (-9) through the bushed holes and Heim bearing common to the White Rod.

Point A

For the L/H White Rod, any gap at Point A when the dog-leg/fitting is not nested within the tool’s cutout will indicate that the L/H White Rod is moved aft, away from the FCT web when installed in the aircraft. For the R/H White

Rod, any gap at Point A when the dog-leg/fitting is not nested within the tool’s cutout will indicate the RH White Rod is moved forward, away from the floor support column.

iii. Inspect for a gap at Point A, as shown in Figure 3.

1. Any gap in excess of 0.021-inch is indicative of the Heim bearing being offset greater than 0.030-inch from the White Rod tube’s centerline and is cause for rejection and replacement of the White Rod.

Figure 4. Inspection of gap at Point B

5. With White Rod pinned in the JX34TA00104-1 inspection tool, insert Pin, P/N JX34TA00104-7, into the unbushed hole of inspection tool. Pin should not contact dog-leg/fitting. Remove pin, twist white-rod and inspection tool 180 degrees, insert pin (-7) into opposite unbushed hole of inspection tool. Pin should not contact dog-leg/fitting.

a. If the pin contacts either surface of dog-leg/fitting, the White Rod is bent and is cause for rejection and replacement of the White Rod.

Point B

Text1: C/W :

2ZQ00B, 2ZQ00S, 2ZQ00X, 2PN00P, 2PT00E, 2PC00A

INFO :

2ZQ00Q

Text2: 12 JAN 2017

T-34 LES T34-0022

25-100, WP 013-01, paragraph 13-4b.

UNITED STATES OF AMERIC

RTMENT OF DEFEN

SE

LES/JX T-34 0023

Date: August 3, 2016

SUBJECT: Maintenance Requirements Exclusion List

IDENTIFICATION: LES/JX T-34 0023

SYSTEM: Airframe

WORK UNIT CODE: N/A

CLASSIFICATION: Conditional. For T-34C aircraft requiring a phase inspection signoff during Aircraft Condition Inspection (ACI).

REFERENCES: (a) NAVAIR 01-50-T34C-600-6-4.1, T-34C Aircraft Phase Inspection Manual, FIRST (Phase 1) 100-Hour Interval Detailed Inspection.

(b) NAVAIR 01-50-T34C-600-6-4.2, T-34C Aircraft Phase Inspection Manual, SECOND (Phase 2) 100-Hour Interval Detailed Inspection.

ENCLOSURES: None

1. PURPOSE: To clearly identify phase inspection requirements that shall be satisfied during the completion of ACI if the applicable phase inspection is to be signed off concurrently with the ACI.

2. CANCELLATION: N/A

3. BACKGROUND: The accomplishment of phase inspections is not a requirement of ACI. However, phase inspections may be conducted concurrently with the ACI at the request of the reporting custodian and the approval of the controlling custodian.

6. SPECIAL CERTIFICATION, TRAINING, OR SKILLS REQUIRED: None

7. SPECIAL TOOLS AND TEST EQUIPMENT: None

8. SPECIAL MATERIALS: None

9. EFFECTIVE DATE: As indicated on the Fleet Readiness Center Southeast (FRCSE) Technical Data Cover Sheet as affixed.

August 3, 2016

The following instructions identify phase inspection requirements that shall be satisfied during the completion of ACI if the applicable phase inspection is to be signed off concurrently with the ACI.

10.1. The following tasks must be accomplished IAW reference (a) to complete the FIRST 100-HOUR INTERVAL DETAILED INSPECTION requirements:

10.1.1. Section A, subparagraphs 1 through 5

10.1.2. Section B, subparagraphs 7.2, 7.3, 13.5, and 16.4

10.1.3. Section C, subparagraph 4 and 8

10.1.4. Section D, subparagraphs 1.3, 1.4, and 2 through 10

10.1.5. Section E

10.2. The following tasks must be accomplished IAW reference (b) to complete the SECOND 100-HOUR INTERVAL DETAILED INSPECTION requirements:

10.2.1. Section A, subparagraphs 1 through 5

10.2.2. Section B, subparagraphs 9.4, 11, and 12

10.2.3. Section C, subparagraphs 1 and 5

10.2.4. Section E, subparagraphs 2, 3, 5, 10, and 13.1

10.2.5. Section F, subparagraphs 9 and 10.1

10.2.6. Section I

11. LOGBOOK ENTRY:

11.1. If the First 100-Hour Interval Detailed Inspection requirements have been performed IAW paragraph 10.1, the following shall be entered into the aircraft logbook: “Phase inspection requirements for the FIRST 100-HOUR INTERVAL DETAILED INSPECTION per NAVAIR 01-50-T34C-600-6-4.1 were satisfied during the completion of ACI [date].

11.2. If the Second 100-Hour Interval Detailed Inspection requirements have been performed IAW paragraph 10.2, the following shall be entered into the aircraft logbook: “Phase inspection requirements for the SECOND 100-HOUR INTERVAL DETAILED INSPECTION per NAVAIR 01-50-T34C-600-6-4.2 were satisfied during the completion of ACI [date].

August 3, 2016

James Harper/Code 4.3.3.2

Justin Hirt/Code 4.3.3.2 Structures Sub-Team Lead

David Pfeffer/Code 4.1.1.1

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Text1: C/W :

2ZQ00B, 2ZQ00X, 2XGA00

INFO :

2ZQ000, 2ZQ00Q

Text2: 23 AUG 2016

T-34 LES T34-0023

Decals Available

See page 1

Type Title Serial Number Due Interval Basis Early Dev

Late Dev

Curr Count

Remaining Over due

Engine Serial #: PWV-58182 Basis TSN TSO Flt Hours 13,670.30 2,213.30

Serial Number: N865NA TEC: AZNJ Basis TSN Flt Hours 5,918.50 Landings 15,548.00

IN

Routine (30 Day) Inspection (Butler) 37052 21-Sep-19 30 DA 8 0 2.00 0.00 Routine (30 Day) Inspection (Butler) 37053 21-Sep-19 30 DA 8 0 2.00 0.00 Routine (30 Day) Inspection (MBU-12/P) (Primary) T-34-1 21-Sep-19 30 DA 8 0 2.00 0.00 Routine (30 Day) Inspection (MBU-12/P) (Primary) T-34-2 21-Sep-19 30 DA 8 0 2.00 0.00 180 DAY OXYGEN REGULATOR INSPECTION N865NA 05-Oct-19 180 DA 30 0 16.00 0.00

1 MONTH ENGINE ROTOR COMPONENTS CYCLE

UPDATE

PWV-58182 05-Oct-19 1 MO 5 0 16.00 0.00

25 HOUR ENGINE OIL SAMPLE PWV-58182 5938.1 25 FH 5 0 13670.30 19.60 0.00

30 DAY NAV Data Update N865NA 10-Oct-19 30 DA 3 0 21.00 0.00 56 DAY TERRAIN DATA UPDATE N865NA 10-Oct-19 56 DA 5 0 21.00 0.00 30 Day Accelerometer Reading N865NA 11-Oct-19 30 DA 3 0 22.00 0.00 12 MONTH AIRCRAFT COMPASS SYSTEM N865NA 31-Oct-19 12 MO 36 0 42.00 0.00 Parachute(180 Day) Repack (Butler) 37052 13-Nov-19 180 DA 30 0 55.00 0.00 Parachute(180 Day) Repack (Butler) 37053 18-Nov-19 180 DA 30 0 60.00 0.00 300 HOUR FLAP MOTOR GEARBOX LUBE/REPACK 168 6012.5 300 FH 30 0 5743.00 94.00 0.00

100 HOUR/18 MONTH 2ND DETAILED INSPECTION

(PHASE)

N865NA 6050.8 200 FH 10 0 5918.50 132.30 0.00

Aircraft Weight and Balance N865NA 11-Mar-20 2 YR 73 0 174.00 0.00 ANNUAL WING BOLT CHECK AND LUBE N865NA 31-Mar-20 12 MO 30 0 194.00 0.00

24 MONTH RECERT ALTIMETER, TRANSPONDER &

PITOT STATIC SYSTMS

N865NA 30-Apr-20 24 MO 72 0 224.00 0.00

T-34 Annual MD Review (OE) N865NA 30-Apr-20 12 MO 36 0 224.00 0.00

ANNUAL LUBRICATION OF THE RUDDER BUSS SHAFT

& LOWER ROD ENDS

N865NA 31-May-20 12 MO 30 0 255.00 0.00

ANNUAL CLEANING & RE-PRESERVATION OF A/C

SLING ATTACH POINTS

N865NA 31-Jul-20 12 MO 36 0 316.00 0.00

ANNUAL NDI INSPECTION OF THE PYLON MOUTING

HOLES

N865NA 15-Aug-20 12 MO 36 0 331.00 0.00

MD

MDCd: 1671 Rev: 1 SB - 1671R1 OIL - FILLER - TUBE

FLANGED ASSEMBLY AND CAP - REPLACEMENT OF

PWV-58182 20-Jun-20 0 0 275.00 0.00

*Deferred until 20 Jun 2020 MDCd: 1671 Rev: 1 SB - 1671R1 OIL - FILLER - TUBE

FLANGED ASSEMBLY AND CAP - REPLACEMENT OF

PWV-58182 20-Jun-20 0 0 13670.30 275.00 0.00

*Deferred until 20 Jun 2020

SL

EMERGENCY LOCATOR TRANSMITTER (ELT),

BATTERY

364569-087 30-Nov-19 3 YR 109 0 72.00 0.00

(All times shown in (UTC-08:00) Pacific Time (US & Canada) )

Selection Criteria: TEC: AZNJ, Days: 365, FH: 134.92, CY: 10, LA: 348.00, OH: 10, FE: 10

Maintenance Forecasting Page 1 of 1Date Generated: 19-Sep-19 12:09 tmmatth1

Highlight

NAVAIR PMA-273 T-34C ACI

NAVAIR T-34C ACI

AIRCRAFT CONDITION INSPECTION

U.S. NAVY MODEL T-34C

Published by direction

Of

Commander, Naval Air Systems Command

20 FEB 2019

LIST OF EFFECTIVE PAGES

Insert latest changed pages; dispose of superseded pages in accordance with applicable regulations.

On a changed page, the portion of the text affected by the latest change is indicated by a vertical line in the outer margin of the page. Change pages without a black vertical line are a result of text shift from page to page or non-technical corrections.

DATE OF ISSUE

ORIGINAL .........0............ 18 March 1988

CHANGE ............1............ 15 September 1988

REISSUE ............0............ 31 March 1994

CHANGE ............1............ 20 October 1994

REISSUE ............0............ 01 May 2000

REISSUE ............0............ 31 May 2016

REISSUE……….0……….20 FEB 2019

TABLE OF CONTENTS

Section/paragraph Page

I GENERAL INSTRUCTIONS 1-1

1-1 SCOPE 1-1

1-1.1 General 1-1

1-1.2 Contents 1-1

1-1.3 Change Recommendations 1-3

1-2 AIRCRAFT CONDITION INSPECTION INTERVALS 1-3

1-3 DEFINITIONS 1-3

1-4 MAINTENANCE REFERENCES 1-10

1-4.1 CNO Procedures 1-11

1-4.2 NAVAIR Instructions 1-11

1.4-3 Navy Publications 1-11

1-4.4 Military Specifications 1-12

1-4.5 Military Standards 1-13

1-4.6 Publications 1-13

1-4.7 Federal Aviation Regulations 1-14

1-4.8 Advisory Circulars 1-14

1-4.9 Airworthiness Directives 1-14

1-4.10 Fleet Readiness Center Southeast (FRCSE) Documents 1-15

1-4.11 Program Management Activity (PMA) 273 Directives 1-16

1-4.12 Miscellaneous Documents 1-16

II AIRCRAFT CONDITION INSPECTION (ACI) REQUIREMENTS 2-1

2-1 GENERAL MAINTENANCE STANDARDS 2-1

2-1.1 General Requirements 2-1

2-1.2 Defect Correction Criteria 2-2

2-1.3 Rework Procedures 2-2

2-1.4 Aircraft Records Maintenance 2-3

2-1.5 Technical Directive Compliance 2-3

2-1.6 Ground Handling, Operation and Safety Precautions 2-4

2-1.7 Structural Repairs 2-4

2-1.8 Nondestructive Inspection Processes 2-5

2-1.9 Self-locking Nuts 2-5

2-1.10 Torque Requirements 2-5

2-1.11 Replacement Parts and Substitutions 2-5

2-1.12 Lock Wiring 2-6

2-1.13 Anti-friction Bearings 2-6

2-1.14 Tubing 2-6

2-1.15 Flexible Hose Assemblies 2-7

2-1.16 Protective Closures 2-7

2-1.17 Identification of Piping 2-7

2-1.18 Packings, Gaskets, and Seals 2-7

2-1.19 Riveting 2-7

2-1.20 Tolerances 2-7

2-1.21 Electrical Wiring 2-8

2-1.22 Usage and Handling of Gases 2-8

2-1.23 Report Requirements 2-8

2-1.24 Scheduled Component Removal/Replacement Criteria 2-9

2-1.25 Unscheduled Component Rework 2-9

Section/Paragraph Page

2-1.26 Engineering Support Requirements 2-9

2-1.27 Pre-delivery Requirements (Operating Activity) 2-10

2-1.28 Ballistic Devices 2-10

2-1.29 Thread Compound 2-10

2-1.30 Non-standard Installations 2-10

2-2 INDUCTION INTO ACI REQUIREMENTS 2-11

2-2.1 Aircraft Record Analysis 2-11

2-2.2 Aircraft Equipment Inventory 2-11

2-2.3 Operational Test 2-11

2-3 AIRCRAFT & ENGINE CLEANING REQUIREMENT 2-12

2-3.1 Cleaning 2-12

2-3.2 Paint System 2-13

2-3.3 Corrosion Removal and Surface Treatment 2-13

2-3.4 Surface Restoration 2-14

2-3.5 Preservation 2-15

2-4 DISASSEMBLY 2-16

2-4.1 Disassembly, General 2-16

2-4.2 Disassembly, Specific 2-16

2-4.3 Examination During Disassembly 2-17

2-5 STRUCTURAL AND ZONAL INSPECTION

REQUIREMENTS 2-17

2-5.1 General 2-17

2-5.2 Wing Assembly and Fuel Tank 2-18

2-5.3 Wing Leading Edge and Fuel Tank 2-19

2-5.4 Flap 2-20

2-5.5 Aileron 2-20

2-5.6 Wing Tip 2-21

2-5.7 Vertical Stabilizer 2-21

2-5.8 Rudder 2-21

2-5.9 Horizontal Stabilizer 2-21

2-5.10 Elevator 2-22

2-5.11 Forward Fuselage, External 2-22

2-5.12 Mid Fuselage, External 2-23

2-5.13 Aft Fuselage, External 2-23

2-5.14 Forward Fuselage and Nose Wheel Well, Internal 2-23

2-5.15 Cockpit and Canopy, Internal 2-24

2-5.16 Aft Fuselage, Internal 2-26

2-5.17 Nose Landing Gear Doors 2-26

2-5.18 Nose Landing Gear 2-27

2-5.19 Main Landing Gear Doors 2-28

2-5.20 Main Landing Gear 2-28

2-6 SYSTEMS AND COMPONENTS 2-30

2-6.1 General 2-30

2-6.2 Flight Controls 2-31

2-6.3 Fuel, Power Plant and Propeller 2-37

2-6.4 Landing Gear 2-37

2-7 ZONE INSPECTION PROCEDURES AND

ZONE DESCRIPTIONS 2-37

2-7.1 General 2-37

2-7.2 Procedure 2-38

2-7.3 Zone Inspection Requirements 2-38

2-7.4 Zonal Description 2-39

III ACI CHECK FLIGHT AND ACCEPTANCE REQUIREMENTS 3-1

3-1 FINAL PROCESSING 3-1

3-1.1 Operational Check 3-1

3-1.2 Weight and Balance 3-1

3-1.3 Logs and Records 3-1

3-1.4 Servicing and Lubrication 3-2

3-1.5 Power Plant Turn-up 3-2

3-1.6 Compass Calibration 3-2

3-2 CHECK FLIGHT 3-3

3-2.1 Daily/Turnaround Inspection 3-3

3-2.2 Functional Checkflight and Acceptance 3-3

3-2.3 Acceptance Processing 3-3

IV COMPONENT REMOVAL/REPLACEMENT SCHEDULE 4-1

4-1 GENERAL 4-1

V MAINTENANCE REQUIREMENTS EXCLUSION LIST 5-1

5-1 GENERAL 5-1

5-2 SPECIFIC REQUIREMENTS 5-1

VI ACI REPORT REQUIREMENTS 6-1

6-1 MAINTENANCE HISTORY SUMMARY REPORT 6-1

6-1.1 General 6-1

6-1.2 Specific Report Requirements 6-1

VII STRUCTURAL SAMPLING REPORTING FORMS REQUIREMENTS 7-1

7-1 GENERAL 7-1

7-1.1 Specific Report Requirements 7-2

VIII FUNCTIONAL SAMPLING REPORTING REQUIREMENTS 8-1

8-1 GENERAL 8-1

8-1.1 Specific Report Requirements 8-1

1-1

SECTION I

GENERAL INSTRUCTIONS

1-1 SCOPE:

1-1.1 GENERAL:

a. This specification establishes the Aircraft Condition Inspection (ACI) requirements for the T-34C aircraft.

b. The ACI requirements provide for airframe, component, and system inspection, deficiency identification and correction, preventive maintenance, modification and technical directive compliance. ACI requirements are expected to restore aircraft subjected to this process to a condition which can be maintained at Field level to ensure a high level of operational availability for the duration of the designed service period. These requirements also provide interim support during the total service life and include but are not limited to:

(1) A thorough and comprehensive inspection of selected aircraft structure, flight essential systems and components by appropriate inspection methods, correcting defects and repairing as required to ensure serviceability until next sequential ACI induction.

(2) Incorporation of all authorized technical directives.

(3) Replacement of depot level time change components which will exceed specified replacement intervals prior to next scheduled ACI.

c. Adjustments, checks, test, repairs, inspections, component rework and preventive maintenance and the rework procedures coincidental thereto shall be accomplished in accordance with applicable directives and publications as directed by this specification.

1-1.2 CONTENTS:

a. Section I of this specification provides general instructions relative to: (1) the purpose and scope of ACI, (2) specification revision information, (3) ACI intervals, (4) definitions of the terminology of Aircraft Condition Inspection, and

(5) maintenance publications and documents required to perform ACI.

1-2

b. Section II of this specification contains general and specific rework requirements;

standards, guidelines, instructions, inspections, tests and rework to be complied with and accomplished by the Rework Activity. Each requirement shall be complied with as an item of scheduled maintenance at the specified rework or time limitation. At completion of all such repair and rework, the aircraft and its accessories/components shall be completely reassembled, applicable systems rigged, aligned and/or tested in accordance with the specified requirements and the aircraft flight checked in accordance with Section III.

(1) The scheduled maintenance requirements prescribed in this specification comprise the minimum requirements necessary to ensure the timely discovery and correction of actual and/or anticipated defects based on the aircraft class and intended use. Compliance with these requirements is mandatory.

(2) Unscheduled maintenance requirements are those requirements which cannot be directly related to any scheduled requirement. These are only discovered as an incidental result of the following functions which are accomplished as a part of and during the scheduled inspections: (1) review of aircraft logbooks and records, (2) the operational/functional testing of system or (3) inspection of the aircraft and its components during ACI.

c. Section III describes the Post ACI functional check flight requirements to be compiled with prior to the delivery of the reworked aircraft.

d. Section IV is a tabulated listing by aircraft systems of components requiring replacement as a function of aircraft flight hours, unit operating time or cycles, or ACI intervals.

e. Section V is the Maintenance Requirements Exclusions List that identifies all requirements that do not have an equivalent ACI requirement. This list is intended for use to avoid duplication of effort when completion of special/phase/detailed inspection is required upon return to the operating activity.

f. Section VI is the Aircraft Maintenance History Summary Report Requirements.

This section provides general and specific reporting requirements to ensure complete documentation of maintenance performed during ACI.

g. Section VII is the Structural Sampling Report Requirements. These requirements are supplemented by (1) illustrations giving specific locations and (2) forms to report amount and severity of corrosion.

h. Section VIII contains the functional Reporting Requirements. These requirements are supplemented by forms to reports action(s) taken on components during testing.

1-3

1-1.3 CHANGE RECOMMENDATIONS:

a. Recommendations for additions, deletions, or changes to the requirements of this specification are invited and should be submitted to the CNATRA Fleet Support Team (FST), Jacksonville Naval Air Station, 293 Romeo Ave. Building 7H, Second Floor. The FST will forward submitted/logged change recommendations to the T-34C APML at Naval Air Systems Command PMA-273, 48187 Standley Road, BLDG 4010, Patuxent River, MD 20670.

b. Revisions and changes to this specification will be prepared by NAVAIR 4.0 Engineering and promulgated by PMA-273, Patuxent River, MD.

1-2 AIRCRAFT CONDITION INSPECTION INTERVALS:

a. Aircraft Condition Inspection (ACI) for the T-34C aircraft is prescribed initially as a function of the planned operational service life of the aircraft. Operational service life is measured in terms of operational service months accumulated between periods of standard rework.

b. ACI intervals (operational service months per period) of the T-34C Aircraft is 60 months.

c. Service periods, total service life and authorized extensions thereto are established by OPNAVINST 3110.11.

1-3 DEFINITIONS:

a. The purpose of this Glossary is to establish a mutual basis of communication to avoid misinterpretation and distortion of the terminology, and thereby, the intent of the requirements contained in the specification.

b. The terms are defined in the context of their application to the requirements of the specification. Generally accepted interpretations and colloquial usage are unacceptable unless in exact agreement.

c. Terminology used in the specification and not defined in the Glossary shall receive the interpretation as defined by OPNAVINST 4790.2 series.

Abrasion. Abrasion is the condition of wearing away by rubbing or scraping (synonymous with Chafing).

Accessible. Areas exposed by the removal of non-permanent fasteners, access doors, panels, fairing, etc. or other disassembly required by a maintenance requirement which does not involve destructive disassembly unless otherwise specified.

1-4

Accessory. A part, subassembly, or assembly designed for use in conjunction with, or to supplement another assembly, unit, or set that contributes to the effectiveness thereof without extending or varying the basic function of the assembly or set. An accessory may be used for testing, adjusting, or calibrating purposes. Examples are test instrument, recording camera for radar set, headphones, and emergency power supply.

Aircraft Conditional Inspection (ACI). Depot level aircraft maintenance accomplished upon an attainment of a specified number of calendar months of service as designed by OPNAVINST 3110.11.

Airframe. The structural components, including the framework and skin, of such parts as the fuselage, empennage, wings, control surfaces, landing gear (minus wheels and tires) and engine mounts.

Airframe Accessories. The items of equipment that are required for operation of the aircraft and that cannot be considered an integral part of the airframe or engine, such as wheels, brakes, hydraulic equipment, fuel system, de-icing equipment, anti-icing equipment, and other items not an integral part of the airframe, regardless of whether attached to the engine or airframe.

Assembly. Any combination or number of parts or subassemblies joined together to perform a specific function.

Attachment. A part, subassembly, or assembly designed for use in conjunction with another assembly, unit, or set that contributes to the effectiveness thereof by varying the basic function of the assembly or set.

Calibrate. To determine and make required corrections in calibration standards or Precision Measuring Equipment (PME) used in precise measurement or to repair adjust and align equipment so that it functions within assigned tolerances; may consist of the comparison of two instruments, one which is a certified calibration standard of known accuracy, to detect and adjust any discrepancy in the accuracy of the other instrument or PME being compared with the certified calibration standard.

Chafing. The wearing away of material by rubbing or scraping (synonymous with Abrasion).

Check. To compare the characteristics of an item with established standards.

Check Flight, Functional. Airborne operational test performed to determine whether the airframe, power plant, accessories, and other items of equipment are functioning in accordance with predetermined standards when subjected to the intended operating environment.

Checkout. A sequence of functional, operational, and calibration tests to determine the condition and status of a system of element thereof.

1-5

Cleanliness. The state of being free from impurities, impediments, and foreign matter not specified to be applied to the surface in question.

Cognizant Government Representative. The government office (NAVPRO, AFPRO, DCASO, CAO, etc.) delegated the local administration of Naval contracts.

Component. A number of parts or subassemblies, or any combination thereof, joined together to perform a specific function.

Component, Scheduled Removal. Components whose overhaul or replacement schedule is established as a function of service use (flight hours, unit operating time or calendar time, cycle, events, or OSP intervals)

Composite Material. A material composed of two or more different constituents, the combination of which results in a product superior in some mechanical properties to any of its constituents parts.

Concurrent Component Rework. The removal of a defective component from an aircraft, repair of that item concurrent with ACI processing of the aircraft, and reinstallation of that item on the same aircraft.

Configuration Identification. The current approved or conditionally approved technical document for a configuration item as set forth in specifications, drawings, and associated lists and reference documents.

Control Letter. A document prepared by the contractor to track a particular maintenance action or item which does not result in a configuration change.

Control letters do not require government approval.

Corrosion. An action or process which destroys metal by chemical or electrochemical action and converts it into an oxide, hydroxide, or sulfate compound.

Crack. A break, fracture, crevice, or separation in the structure of a part.

Crazing. Fine cracks, which may extend in a network, in plastic material (i.e.

windshields, canopy glass, windows, etc.).

Damage. Impairment of an aircraft/item/part by a physical force.

Defect. Any nonconformance of a unit or part with specified requirements (synonymous with Discrepancy).

Defect, Critical. A defect that constitutes a hazardous or unsafe condition, or as determined by experience or judgment could conceivably become so, relative to its deleterious effect on the prime intended function, safety of flight or mission capability of the aircraft of its operating personnel.

1-6

Defect, Major. A defect, other than critical, that could result in failure, or materially reduce, the usability of the unit or part for its intended purpose.

Defect, Minor. A defect that does not materially reduce or if not corrected will not degrade the usability of the unit or part for its intended purpose, or is a departure from standards which has no significant bearing on the effective use or operation of the unit or part.

Defective. The state of possessing one or more defects.

Deformation. Any disfiguration or change in form or shape from the intended design configuration.

Delamination. A physical break of the bond between the binder material and any two or more plies of laminated panels fabricated of plastic, metal, composite material, or other material.

Detailed Inspection. A thorough examination of the appliances, the aircraft, and components and systems with such disassembly as necessary.

Deterioration. The breakup, eating away, or decomposition of a substance by the action of weather, corrosion, or other environmental conditions.

Discrepancy. Any nonconformance of a unit or part with specified requirements (synonymous with Defect).

Distortion. Any disagreement or change in form or shape from the intended design configuration.

Disturbed System. A system whose installed integrity has been interrupted, broken, or interfered with to the extent that system installation and operation cannot be assured with verification by a functional or operational check or test.

Evidence. Factual data which establishes as the possibility of an existing or impending unsatisfactory condition.

Equipment. A collection of items consisting of parts, subassemblies, components, assemblies, units, groups, sets, subsystems, and systems.

Examination. An element of inspection consisting of investigation, without the use of special laboratory appliances or procedures, of supplies and services to determine conformance to those specified requirements that can be determined by such investigations. Examination is generally nondestructive.

1-7

Exterior Surface. That part of the airframe exposed to the elements when in a “clean” flight configuration, including wing and stabilizer control surface wells (aileron, flap, rudder, and elevator). Does not include landing gear structure, wheel wells, or areas exposed by deflection of slats, vanes, speed brakes, wing folds, etc., or extension of landing gear.

Failure. The inability of an item to perform within previously specified limits.

Fraying. The wearing away by rubbing, usually of woven, braided, or stranded material, which results in a worn ragged appearance.

Groove. Any narrow furrow, depression, or slit on the surface of a part.

Group. A collection of units, assemblies, or subassemblies that is a subdivision of a set or system, but is not capable of performing a complete operational function (see System).

Inclusion. A void or discontinuity in the molecular structure of metal.

Inspect. To perform critical investigation of an item, unit, component, or airframe through the visual, auditory, olfactory and tactile senses, utilizing simple manipulation, gauging and measurements as required for the specific intent of determining its conformance to the assigned specifications within the tolerances permitted and may require partial disassembly of such items.

Inspection. To compare the characteristics of an item with established standards.

Inspection includes, but is not limited to, sight, hearing, smell, touch, taste, and other investigations; simple physical manipulation, gauging and measurement.

The process may require partial disassembly of the item.

Inspection, Visual/Dye-Penetrant. To inspect for cracks first via visual methods and then, if a crack is suspected, confirm or deny presence of crack by use of dye-penetrant technique.

Major Structural Damage. Damage which requires removal or extensive in-place repair, and repair or replacement of airframe structural members.

Modify. To alter in appearance, performance, function, position, or effect.

Nick. Any notch, slit, cut, or chip on the surface of a part.

Overhaul, Component. Rework performed on a component which includes disassembly sufficient to inspect all constituent parts, followed by cleaning, repair, replacement of consumables and defective parts as required, servicing, re-assembly, and checks/tests in accordance with applicable overhaul specifications, instructions and procedures. An overhauled component is capable of performing for its intended service period.

1-8

Part. One piece, or two or more pieces joined together, not normally subject to disassembly without destruction of designed use.

Pitting. Any small, approximately circular indentation, depression, hollow, or scar in the surface of a part; generally the result of corrosion of erosive action.

Quality Assurance. A planned program of actions necessary to provide confidence that processing conforms to established standards.

Refinish. To restore an existing surface finish…