42592 Federal Register / Vol. 75, No. 140 / Thursday, July 22, 2010 / Rules and Regulations 

TABLE 2—CREDIT SERVICE INFORMATION—Continued 

Airbus mandatory service bulletin— Revision— Dated— 

A330–27–3152 ................................................................... 01 ....................................................................................... March 19, 2008. 

A330–27–3152 ................................................................... 02 ....................................................................................... September 23, 2008. 

A340–27–4151 ................................................................... Original ............................................................................... August 9, 2007. 

A340–27–4152 ................................................................... Original ............................................................................... August 9, 2007. 

A340–27–4152 ................................................................... 01 ....................................................................................... March 19, 2008. 

A340–27–5040 ................................................................... Original ............................................................................... August 9, 2007. 

A340–27–5040 ................................................................... 01 ....................................................................................... March 19, 2008. 

Note 1: Airbus should be contacted in 

order to get appropriate information for 

airplanes on which the original delivery date 

of the airplane is unknown to the operator. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(h) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Vladimir 

Ulyanov, Aerospace Engineer, International 

Branch, ANM–116, FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1138; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(i) Refer to MCAI EASA Airworthiness 

Directive 2008–0026, dated February 12, 

2008, and the service information specified 

in Table 1 of this AD, for related information. 

Material Incorporated by Reference 

(j) You must use the service information 

contained in Table 3 of this AD to do the 

actions required by this AD, unless the AD 

specifies otherwise. 

TABLE 3—MATERIAL INCORPORATED BY REFERENCE

Airbus mandatory service bulletin— Revision— Dated— 

A330–27–3151, including Appendix 1 .................................................................................................... 01 March 19, 2008 

A330–27–3152, including Appendices 1 and 2 ...................................................................................... 03 February 22, 2010 

A340–27–4151, including Appendix 1 .................................................................................................... 01 March 19, 2008 

A340–27–4152, including Appendices 1 and 2 ...................................................................................... 02 September 23, 2008 

A340–27–5040, including Appendix 1 .................................................................................................... 02 September 23, 2008 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80, e-mail 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on June 30, 

2010. 

Todd G. Dixon, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–17064 Filed 7–21–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0671; Directorate 

Identifier 2010–NM–142–AD; Amendment 

39–16363; AD 2010–14–18] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767–200, –300, and 

–300F Series Airplanes Powered by 

General Electric or Pratt & Whitney 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to certain Model 767–200, 

–300, and –300F series airplanes. The 


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Federal Register / Vol. 75, No. 140 / Thursday, July 22, 2010 / Rules and Regulations 42593 

existing AD currently requires repetitive 

inspections to detect discrepancies of 

the 8 aft-most fastener holes in the 

horizontal tangs of the midspar fitting of 

the strut, and corrective actions if 

necessary. The existing AD also requires 

repetitive inspections for cracks of the 

closeout angle that covers the 2 aft-most 

fasteners in the lower tang of the 

midspar fitting, and related investigative 

and corrective actions if necessary. The 

existing AD also provides an optional 

terminating action for the repetitive 

inspections. This new AD reduces the 

compliance times for doing the 

inspections. This AD results from 

reports of cracks in the midspar fitting 

tangs. We are issuing this AD to detect 

and correct fatigue cracking in the 

primary strut structure and reduced 

structural integrity of the strut, which 

could result in separation of the strut 

and engine. 

DATES: This AD becomes effective 

August 6, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 6, 2010. 

We must receive any comments on 

this AD by September 7, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6577; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On September 13, 2005, we issued AD 

2005–19–23, amendment 39–14288 (70 

FR 55519, September 22, 2005). That 

AD applies to certain Boeing Model 

767–200, –300, and –300F series 

airplanes. That AD requires repetitive 

inspections to detect discrepancies of 

the eight aft-most fastener holes in the 

horizontal tangs of the midspar fitting of 

the strut, and corrective actions if 

necessary. That AD also requires 

repetitive inspections for cracks of the 

closeout angle that covers the two aftmost fasteners in the lower tang of the 

midspar fitting, and related investigative 

and corrective actions if necessary. That 

AD also provides an optional 

terminating action for the repetitive 

inspections. That AD resulted from a 

report of a crack in a closeout angle that 

covers the two aft-most fasteners in the 

lower tang of the midspar fitting, and 

the discovery of a crack in the lower 

tang of the midspar fitting under the 

cracked closeout angle. The actions 

specified in that AD are intended to 

prevent fatigue cracking in the primary 

strut structure and reduced structural 

integrity of the strut, which could result 

in separation of the strut and engine. 

Actions Since AD Was Issued 

Since we issued that AD, we received 

two reports of cracks in the midspar 

fitting tangs. The first report indicated 

severed upper and lower tangs at the aft 

two fastener locations in the Number 1 

pylon inboard midspar fitting. The 

cracks were found during a routine 

check of a Model 767–300 airplane at 

approximately 92,205 total flight hours 

and 14,969 total flight cycles. This 

airplane had incurred 408 flight cycles 

from the previous inspection. The 

second report indicated cracks in the 

Number 1 pylon inboard midspar fitting 

lower tang, between the aft two fastener 

holes, on a Model 767–300 airplane at 

approximately 94,176 total flight hours 

and 15,405 total flight cycles. This 

airplane had incurred 830 cycles from 

the previous inspection. 

AD 2005–19–23 specified repetitive 

inspection intervals between 1,500 

flight cycles and 16,000 flight cycles, 

depending on the inspection type and 

location. We have determined that the 

affected airplanes must be inspected 

within 400 flight cycles since the 

previous inspection and, for those 

airplanes that have not yet been 

inspected, the compliance time 

threshold of 10,000 total flight cycles 

specified in AD 2005–19–23 must be 

reduced to 8,000 total flight cycles. We 

have also determined that repetitive 

inspection intervals must be reduced to 

400 flight cycles and 6,000 flight cycles, 

depending on the inspection type. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin 767–54A0101, Revision 

5, dated June 29, 2010. We referred to 

Boeing Alert Service Bulletin 767– 

54A0101, Revision 4, dated February 10, 

2005, for doing certain actions required 

by AD 2005–19–23. The procedures in 

Revision 5 are similar to the procedures 

in Revision 4. Revision 5 reduces the 

compliance times for doing the 

procedures. 

We have also reviewed Boeing Alert 

Service Bulletin 767–54A0062, Revision 

6, dated November 5, 2009; and Boeing 

Alert Service Bulletin 767–54A0074, 

Revision 1, dated April 24, 2008; which 

are the latest versions of certain service 

bulletins referred to in AD 2005–19–23 

as additional sources of guidance for 

doing the terminating action. Boeing 

Alert Service Bulletin 767–54A0101, 

Revision 5, dated June 29, 2010, refers 

to Boeing Alert Service Bulletin 767– 

54A0062, Revision 6, dated November 

5, 2009; and Boeing Alert Service 

Bulletin 767–54A0074, Revision 1, 

dated April 24, 2008; as additional 

sources of guidance for doing the 

terminating action in Part 4 of the alert 

service bulletin. 

Other Relevant Rulemaking 

The FAA has issued the following 

ADs that are related to the additional 

sources of guidance specified in this 

AD. 


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TABLE—OTHER RELEVANT RULEMAKING

AD Applicability Related Boeing Service Bulletin AD requirement 

AD 2000–07–05, amendment 39– 

11659 (65 FR 18883, April 10, 

2000).

Certain Boeing Model 767 series 

airplanes.

767–54A0094 ............................... Repetitive inspections to detect 

cracking or damage of the forward and aft lugs of the diagonal brace of the nacelle strut; 

follow-on actions, if necessary; 

and terminating action for the 

repetitive inspections. 

AD 2004–16–12, amendment 39– 

13768 (69 FR 51002, August 17, 

2004).

Certain Boeing Model 767–200, 

–300, and –300F series airplanes powered by Pratt & 

Whitney engines or General 

Electric engines.

767–54–0069, 767–54–0080, 

767–54–0081, and 767– 

54A0094.

Modification of the nacelle strut 

and wing structure. (AD 2004– 

16–12 superseded AD 2001– 

02–07, Amendment 39–12091 

and AD 2001–06–12, Amendment 39–12159.) 

AD 2009–20–09, amendment 39– 

16032 (74 FR 50692, October 1, 

2009).

Certain Boeing Model 767–200, 

–300, and –300F series airplanes.

767–54A0074 ............................... Repetitive inspections for fatigue 

cracking and corrosion of the 

upper link fuse pin of the nacelle struts, and related investigative and corrective actions if 

necessary. 

AD 2010–03–08, amendment 39– 

16192 (75 FR 5677, February 4, 

2010).

Certain Boeing Model 767–200, 

–300, and –300F series airplanes.

767–54A0062, ..............................

767–54–0069 ................................

Repetitive detailed and eddy current inspections to detect 

cracks of certain midspar fuse 

pins, and corrective action if 

necessary. (AD 2010–03–08 

superseded AD 2003–03–02, 

Amendment 39–13026.) 

FAA’s Determination and Requirements 

of This AD 

The unsafe condition described 

previously is likely to exist or develop 

on other airplanes of the same type 

design. For this reason, we are issuing 

this AD to supersede AD 2005–19–23. 

This AD requires accomplishing the 

actions specified in Boeing Alert Service 

Bulletin 767–54A0101, Revision 5, 

dated June 29, 2010, described 

previously, except as discussed under 

‘‘Differences Between the AD and the 

Service Bulletin.’’ 

Differences Between the AD and the 

Service Bulletin 

The service bulletin specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this AD requires 

repairing those conditions in one of the 

following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Steps 4.a. and 4.b. of Part 2 of the 

Work Instructions of Boeing Alert 

Service Bulletin 767–54A0101, Revision 

5, dated June 29, 2010, specify actions 

if cracking is found and the hole size is 

either greater than 0.5322 inch or less 

than 0.5322 inch but not if the hole size 

equals 0.5322 inch. This AD specifies 

that if cracking is found and the hole 

size equals 0.5322 inch, then the 

terminating action specified in step 4.a. 

of Part 2 of the Work Instructions of 

Boeing Alert Service Bulletin 767– 

54A0101, Revision 5, dated June 29, 

2010, must be accomplished. 

Interim Action 

We consider this AD interim action. 

We are currently considering additional 

rulemaking to expand the inspection 

area. 

FAA’s Justification and Determination 

of the Effective Date 

Fatigue cracking in the primary strut 

structure could result in reduced 

structural integrity of the strut and 

consequent separation of the strut and 

engine. Because of our requirement to 

promote safe flight of civil aircraft and 

thus, the critical need to ensure the 

structural integrity of the pylon 

structure and midspar fittings and the 

short compliance time involved with 

this action, this AD must be issued 

immediately. 

Because an unsafe condition exists 

that requires the immediate adoption of 

this AD, we find that notice and 

opportunity for prior public comment 

hereon are impracticable and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2010–0671; Directorate Identifier 2010– 

NM–142–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this AD. We will consider all 

comments received by the closing date 

and may amend this AD because of 

those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 


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Federal Register / Vol. 75, No. 140 / Thursday, July 22, 2010 / Rules and Regulations 42595 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

See the ADDRESSES section for a location 

to examine the regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (14 CFR part 39) as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14288 (70 

FR 55519, September 22, 2005) and by 

adding the following new airworthiness 

directive (AD): 

2010–14–18 The Boeing Company: 

Amendment 39–16363. Docket No. 

FAA–2010–0671; Directorate Identifier 

2010–NM–142–AD. 

Effective Date 

(a) This AD becomes effective August 6, 

2010. 

Affected ADs 

(b) This AD supersedes AD 2005–19–23, 

Amendment 39–14288. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 767–200, –300, and –300F 

series airplanes, certificated in any category; 

as identified in Boeing Alert Service Bulletin 

767–54A0101, Revision 5, dated June 29, 

2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Unsafe Condition 

(e) This AD results from reports of cracks 

in the midspar fitting tangs. The Federal 

Aviation Administration is issuing this AD to 

detect and correct fatigue cracking in the 

primary strut structure and reduced 

structural integrity of the strut, which could 

result in separation of the strut and engine. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Note 1: Notwithstanding any inspection 

done in accordance with AD 2005–19–23, 

inspect within the compliance times 

specified in this AD. 

Initial Inspection 

(g) At the applicable time specified in 

paragraph (h) of this AD: Do the actions 

specified in either paragraph (g)(1) or (g)(2) 

of this AD. 

(1) Do a detailed inspection for cracking of 

the 8 aft-most fastener holes in the horizontal 

tangs of the midspar fitting of the strut, and 

a surface high frequency eddy current (HFEC) 

inspection for cracking of the closeout angle 

that covers the 2 aft-most fasteners in the 

lower tang of the midspar fitting, in 

accordance with Part 1, ‘‘Detailed Inspection 

of Midspar Fitting and Surface High 

Frequency Eddy Current (HFEC) Inspection 

of Closeout Angle,’’ of the Work Instructions 

of Boeing Alert Service Bulletin 767– 

54A0101, Revision 5, dated June 29, 2010. 

(2) Do an open-hole HFEC inspection for 

cracking of each fastener hole, inspect to 

determine the size of each fastener hole, and 

do all applicable related investigative and 

corrective actions, in accordance with Part 2, 

‘‘Open Hole HFEC Inspection,’’ of the Work 

Instructions of Boeing Alert Service Bulletin 

767–54A0101, Revision 5, dated June 29, 

2010, except as required by paragraphs (m) 

and (n) of this AD, and except as provided 

by paragraph (p) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. 

(h) At the applicable time specified in 

paragraph (h)(1) or (h)(2) of this AD, do the 

actions specified in paragraph (g) of this AD. 

(1) For airplanes on which an inspection 

(any Part 1 or Part 2 inspection) has not been 

done in accordance with any service bulletin 

listed in Table 1 of this AD as of the effective 

date of this AD: Prior to the accumulation of 

8,000 total flight cycles, or within 90 days 

after the effective date of this AD, whichever 

occurs later, do the actions specified in 

paragraph (g) of this AD. 

TABLE 1—SERVICE BULLETINS

Service Bulletin Revision Date 

Boeing Alert Service Bulletin 767–54A0101 .......................................................... 4 ............................................................. February 10, 2005. 

Boeing Alert Service Bulletin 767–54A0101 .......................................................... 5 ............................................................. June 29, 2010. 

Boeing Service Bulletin 767–54A0101 ................................................................... 2 ............................................................. January 10, 2002. 

Boeing Service Bulletin 767–54A0101 ................................................................... 3 ............................................................. September 5, 2002. 

(2) For airplanes on which any inspection 

(any Part 1 or Part 2 inspection) has been 

done in accordance with any service bulletin 

listed in Table 1 of this AD as of the effective 

date of this AD: Within 400 flight cycles after 

doing the most recent inspection or within 90 

days after the effective date of this AD, 

whichever occurs later, do the actions 

specified in paragraph (g) of this AD. 

Repetitive Inspections 

(i) If, during any detailed and surface HFEC 

inspection specified by paragraph (g)(1) of 

this AD, no cracking is found, do the actions 

specified in either paragraph (i)(1) or (i)(2) of 

this AD. 

(1) Repeat the inspections specified in 

paragraph (g)(1) of this AD thereafter at 

intervals not to exceed 400 flight cycles. 

(2) Within 400 flight cycles after doing the 

most recent inspections specified in 

paragraph (g)(1) of this AD, do the actions 

specified in paragraph (g)(2) of this AD and 

repeat thereafter at intervals not to exceed 

6,000 flight cycles. 

(j) If, during the actions specified by 

paragraph (g)(2) of this AD, the terminating 

action specified in Part 4 of the Work 

Instructions of Boeing Alert Service Bulletin 


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42596 Federal Register / Vol. 75, No. 140 / Thursday, July 22, 2010 / Rules and Regulations 

767–54A0101, Revision 5, dated June 29, 

2010, is not done, do the actions specified in 

either paragraph (j)(1) or (j)(2) of this AD. 

(1) Within 6,000 flight cycles after doing 

the actions specified in paragraph (g)(2) of 

this AD, do the inspections specified in 

paragraph (g)(1) of this AD and repeat the 

inspections thereafter at intervals not to 

exceed 400 flight cycles. 

(2) Repeat the actions specified in 

paragraph (g)(2) of this AD thereafter at 

intervals not to exceed 6,000 flight cycles. 

Corrective Actions for Inspections Done per 

Paragraph (g)(1) of This AD 

(k) If, during any inspection specified by 

paragraph (g)(1) of this AD, any crack is 

found in the midspar fitting tangs, before 

further flight, do the actions specified in 

paragraph (k)(1) or (k)(2) of this AD. 

(1) Do the terminating action specified in 

Part 4 of the Work Instructions of Boeing 

Alert Service Bulletin 767–54A0101, 

Revision 5, dated June 29, 2010, except as 

required by paragraph (m) of this AD. 

Accomplishment of this paragraph 

terminates the requirements of this AD. 

(2) Replace the midspar fitting of the strut 

with a new part, or repair in accordance with 

a method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA. 

Within 8,000 flight cycles after doing the 

replacement, do the actions specified in 

either paragraph (k)(2)(i) or (k)(2)(ii) of this 

AD. 

(i) Do the inspections specified in 

paragraph (g)(1) of this AD and repeat the 

inspections thereafter at intervals not to 

exceed 400 flight cycles. 

(ii) Do the actions specified in paragraph 

(g)(2) of this AD and repeat the actions 

thereafter at intervals not to exceed 6,000 

flight cycles. 

(l) If, during any surface HFEC inspection 

specified by paragraph (g)(1) of this AD, any 

crack is found in the closeout angle, before 

further flight, do the open-hole HFEC 

inspection for cracking and all applicable 

related investigative and corrective actions, 

in accordance with Part 2, ‘‘Open Hole HFEC 

Inspection,’’ and step 4.b.(2) of Part 1, 

‘‘Detailed Inspection of Midspar Fitting and 

Surface High Frequency Eddy Current 

(HFEC) Inspection of Closeout Angle,’’ of the 

Work Instructions of Boeing Alert Service 

Bulletin 767–54A0101, Revision 5, dated 

June 29, 2010, except as required by 

paragraphs (m) and (n) of this AD, and except 

as provided by paragraph (p) of this AD. If 

the terminating action specified in Part 4 of 

the Work Instructions of Boeing Alert Service 

Bulletin 767–54A0101, Revision 5, dated 

June 29, 2010, is not done, do the actions 

specified in either paragraph (l)(1) or (l)(2) of 

this AD. 

(1) Within 6,000 flight cycles after doing 

the actions specified in paragraph (l) of this 

AD, do the inspections specified in 

paragraph (g)(1) of this AD and repeat the 

inspections thereafter at intervals not to 

exceed 400 flight cycles. 

(2) Within 6,000 flight cycles after doing 

the actions specified in paragraph (l) of this 

AD, do the actions specified in paragraph 

(g)(2) of this AD, and repeat the actions 

thereafter at intervals not to exceed 6,000 

flight cycles. 

Service Bulletin Exceptions 

(m) Where Boeing Alert Service Bulletin 

767–54A0101, Revision 5, dated June 29, 

2010, specifies that the manufacturer may be 

contacted for disposition of repair 

conditions: Before further flight, accomplish 

the repair using a method approved in 

accordance with the procedures specified in 

paragraph (r) of this AD. 

(n) If, during any open-hole HFEC 

inspection required by paragraph (g)(2) or (l) 

of this AD, any crack is found in the midspar 

fitting and the hole size is 0.5322 inch, before 

further flight, do the terminating action 

specified in paragraph (k)(1) of this AD. 

Optional Terminating Action 

(o) Doing the terminating action specified 

in Part 4 of the Work Instructions of Boeing 

Alert Service Bulletin 767–54A0101, 

Revision 5, dated June 29, 2010, terminates 

the requirements of this AD. 

Note 2: Boeing Alert Service Bulletin 767– 

54A0101, Revision 5, dated June 29, 2010, 

refers to the Boeing service bulletins in Table 

2 of this AD as additional sources of 

guidance for doing the terminating action in 

paragraphs (k) and (o) of this AD. 

TABLE 2—ADDITIONAL SOURCES OF GUIDANCE

Boeing Service 

Bulletin Revision level Date Title 

767–54–0052 .......... Original .................. June 11, 1992 ....... Nacelles/Pylons—Strut—Aft Lower Spar—Fastener Corrosion—Inspection 

and Replacement. 

767–54–0061 .......... 2 ............................ November 23, 

1999.

Nacelles/Pylons—Wing–to–Strut Attach Fittings—Lower Spar Bushing Inspection and Replacement. 

767–54–0069 .......... 2 ............................ August 31, 2000 ... Nacelles/Pylons—Midspar Fitting—Underwing Sideload Fitting—Fuse Pin Replacement and Wing Rework. 

767–54–0072 .......... Original .................. March 13, 1997 ..... Nacelles/Pylons—Strut Attach Upper Link—Upper Link Inspection, Rework or 

Replacement. 

767–54–0080 .......... 1 ............................ May 9, 2002 .......... Nacelles/Pylons—Pratt and Whitney Powered Airplanes—Nacelle Strut and 

Wing Structure Modification. 

767–54–0081 .......... 1 ............................ February 7, 2002 .. Nacelles/Pylons—General Electric Powered Airplanes—Nacelle Strut and 

Wing Structure Modification. 

767–54A0062 .......... 6 ............................ November 5, 2009 Nacelles/Pylons—Strut Attach Fuse Pins—Midspar Fuse Pin Inspection and 

Replacement. 

767–54A0074 .......... 1 ............................ April 24, 2008 ....... Nacelles/Pylons—Strut Attach Fuse Pins—Upper link Fuse Pin Inspection/Replacement. 

767–54A0094 .......... 2 ............................ February 7, 2002 .. Nacelles/Pylons—Strut—to—Wing Attachment—Diagonal Brace Inspection/ 

Rework/Replacement. 

767–57–0063 .......... 1 ............................ November 30, 

2000.

Wings—Side Load Underwing Fitting —Inspection/Rework. 

Note 3: Certain service bulletins referenced 

in Table 2 of this AD are related to the ADs 

listed in Table 3 of this AD. 

TABLE 3—OTHER RELEVANT RULEMAKING

AD Applicability Related Boeing 

Service Bulletin AD requirement 

AD 2000–07–05, 

amendment 39– 

11659.

Certain Boeing 

Model 767 series 

airplanes.

767–54A0094 ........ Repetitive inspections to detect cracking or damage of the forward and aft 

lugs of the diagonal brace of the nacelle strut; follow-on actions, if necessary; and terminating action for the repetitive inspections. 


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Federal Register / Vol. 75, No. 140 / Thursday, July 22, 2010 / Rules and Regulations 42597 

TABLE 3—OTHER RELEVANT RULEMAKING—Continued 

AD Applicability Related Boeing 

Service Bulletin AD requirement 

AD 2004–16–12, 

amendment 39– 

13768.

Certain Boeing 

Model 767–200, 

–300, and –300F 

series airplanes 

powered by Pratt 

& Whitney engines or General 

Electric engines.

767–54–0069, 

767–54–0080, 

767–54–0081, 

and 767– 

54A0094.

Modification of the nacelle strut and wing structure. 

AD 2009–20–09, 

amendment 39– 

16032.

Certain Boeing 

Model 767–200, 

–300, and –300F 

series airplanes.

767–54A0074 ........ Repetitive inspections for fatigue cracking and corrosion of the upper link fuse 

pin of the nacelle struts, and related investigative and corrective actions if 

necessary. 

AD 2010–03–08, 

amendment 39– 

16192.

Certain Boeing 

Model 767–200, 

–300, and –300F 

series airplanes.

767–54A0062, 

767–54–0069.

Repetitive detailed and eddy current inspections to detect cracks of certain 

midspar fuse pins, and corrective action if necessary. 

Optional Corrective Action for Paragraph 

(g)(2) or (l) of This AD 

(p) In lieu of doing the related investigative 

and corrective actions required by paragraph 

(g)(2) or (l) of this AD, before further flight, 

replace the midspar fitting of the strut with 

a new part, or repair in accordance with a 

method approved by the Manager, Seattle 

Aircraft Certification Office (ACO), FAA. 

Within 8,000 flight cycles after doing any 

replacement, do the actions specified in 

either paragraph (p)(1) or (p)(2) of this AD. 

(1) Do the inspections specified in 

paragraph (g)(1) of this AD and repeat the 

inspections thereafter at intervals not to 

exceed 400 flight cycles. 

(2) Do the actions specified in paragraph 

(g)(2) of this AD and repeat the actions 

thereafter at intervals not to exceed 6,000 

flight cycles. 

Terminating Action Accomplished per 

Previous Issues of Service Bulletin 

(q) Doing the terminating action specified 

in Part 4 of the Work Instructions of any 

service bulletin listed in Table 4 of this AD 

before the effective date of this AD is 

acceptable for compliance with the 

requirements of this AD. 

TABLE 4—CREDIT SERVICE BULLETINS FOR TERMINATING ACTION

Service Bulletin Revision Date 

Boeing Alert Service Bulletin 767–54A0101 ......................................................... Original .................................................. September 23, 1999. 

Boeing Alert Service Bulletin 767–54A0101 ......................................................... 4 ............................................................ February 10, 2005. 

Boeing Service Bulletin 767–54A0101 .................................................................. 1 ............................................................ February 3, 2000. 

Boeing Service Bulletin 767–54A0101 .................................................................. 2 ............................................................ January 10, 2002. 

Boeing Service Bulletin 767–54A0101 .................................................................. 3 ............................................................ September 5, 2002. 

Alternative Methods of Compliance 

(AMOCs) 

(r)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to Attn: Berhane Alazar, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6577; fax (425) 917–6590. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(s) You must use Boeing Alert Service 

Bulletin 767–54A0101, Revision 5, dated 

June 29, 2010, to do the actions required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on July 9, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–17611 Filed 7–21–10; 8:45 am] 

BILLING CODE 4910–13–P 


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