Federal Register / Vol. 77, No. 209 / Monday, October 29, 2012 / Proposed Rules 65503 

the wiring, and do all associated actions, per 

the Accomplishment Instructions of Boeing 

Service Bulletin A3500, Revision 1, dated 

April 26, 2001. The associated actions 

include performing a general visual 

inspection of the area around each fuel boost 

pump and override pump for evidence of a 

fuel leak; finding the source of any fuel leak 

and repairing the affected area; replacing the 

conduit, if required; and performing a 

detailed visual inspection of the wiring 

installed in the conduit for evidence of 

electrical arcing or a fuel leak, or exposed 

copper wire. If replacement of the conduit is 

deferred per the Accomplishment 

Instructions of Boeing Service Bulletin 

A3500, Revision 1, dated April 26, 2001, 

repeat the inspection for fuel leaks every 500 

flight hours until the conduit is replaced, and 

replace the conduit within 6,000 flight hours 

or 18 months, whichever occurs first. 

(1) For the purposes of this AD, a general 

visual inspection is defined as: ‘‘A visual 

examination of an interior or exterior area, 

installation, or assembly to detect obvious 

damage, failure, or irregularity. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or drop-light, and may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked.’’ 

(2) For the purposes of this AD, a detailed 

visual inspection is defined as: ‘‘An intensive 

visual examination of a specific structural 

area, system, installation, or assembly to 

detect damage, failure, or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at 

intensity deemed appropriate by the 

inspector. Inspection aids such as mirror, 

magnifying lenses, etc., may be used. Surface 

cleaning and elaborate access procedures 

may be required.’’ 

(h) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (b) of AD 2001–17–20, 

Amendment 39–12411 (66 FR 44954, August 

27, 2001), with a new compliance time. After 

replacement of the wiring per paragraph (g) 

of this AD, repeat the detailed visual 

inspection of the wiring for the fuel boost 

pumps and override pumps for damage, such 

as evidence of electrical arcing or exposed 

copper wire, or evidence of a fuel leak. After 

the effective date of this AD, repeat the 

inspection one time at the earlier of the times 

specified in paragraphs (h)(1) and (h)(2) of 

this AD, per the Accomplishment 

Instructions of Boeing Service Bulletin 

A3500, Revision 1, dated April 26, 2001. If 

any electrical arcing or exposed copper wire 

or evidence of a fuel leak is detected during 

any inspection per this paragraph, before 

further flight, do the applicable corrective 

actions (including finding the source of any 

fuel leak and repairing the affected area, 

replacing the wiring, replacing the conduit, 

or installing new Teflon sleeving; as 

applicable) according to the Accomplishment 

Instructions of Boeing Service Bulletin 

A3500, Revision 1, dated April 26, 2001. 

Repeat the inspection thereafter at intervals 

not to exceed 15,000 flight hours. 

(1) Within 30,000 flight hours after the 

most recent inspection. 

(2) At the later of the compliance times 

specified in paragraphs (h)(2)(i) and (h)(2)(ii) 

of this AD. 

(i) Within 15,000 flight hours after the most 

recent inspection. 

(ii) Within 3 years after the effective date 

of this AD. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before 

October 1, 2001 (the effective date of AD 

2001–17–20, Amendment 39–12411 (66 FR 

44954, August 27, 2001)), using Boeing Alert 

Service Bulletin A3500, dated July 27, 2000, 

which is not incorporated by reference in this 

AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Certification 

Office (ACO), FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) AMOCs approved previously in 

accordance with AD 2001–17–20, 

Amendment 39–12411 (66 FR 44954, August 

27, 2001), are approved as AMOCs for this 

AD, except for AMOCS that change the 

inspection frequency. 

(k) Related Information 

(1) For more information about this AD, 

contact Rebel Nichols, Aerospace Engineer, 

Propulsion Branch, ANM–140S, Seattle 

Aircraft Certification Office (ACO), FAA, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone 425–917–6509; fax 425–917– 

6590; email: Rebel.Nichols@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on October 

22, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26480 Filed 10–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1148; Directorate 

Identifier 2012–CE–039–AD] 

RIN 2120–AA64 

Airworthiness Directives; Diamond 

Aircraft Industries GmbH Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for 

Diamond Aircraft Industries GmbH 

Models DA 42, DA 42 M–NG, and DA 

42 NG airplanes. This proposed AD 

results from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as overextension of the main 

landing gear (MLG) shock absorber that 

could lead to the MLG jamming in the 

gear bay and result in damage to the 

aircraft or occupant injury. We are 

issuing this proposed AD to require 

actions to address the unsafe condition 

on these products. 

DATES: We must receive comments on 

this proposed AD by December 13, 

2012. 

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 proposed AD, contact Diamond 

Aircraft Industries GmbH, N.A. OttoStra+e 5, A–2700 Wiener Neustadt, 

Austria, telephone: +43 2622 26700; fax: 

+43 2622 26780; email: 

office@diamond-air.at; Internet: http:// 

www.diamond-air.at. You may review 

copies of the referenced service 

information at the FAA, Small Airplane 


rmajette on DSK2TPTVN1PROD with 
65504 Federal Register / Vol. 77, No. 209 / Monday, October 29, 2012 / Proposed Rules 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

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 proposed 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: 

Mike Kiesov, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 

329–4090; email: mike.kiesov@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–1148; Directorate Identifier 

2012–CE–039–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

regulations.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued AD No.: 2012– 

0174, dated September 4, 2012 (referred 

to after this as ‘‘the MCAI’’), to correct 

an unsafe condition for the specified 

products. The MCAI states: 

An incident was reported where a 

Diamond DA 42 experienced main landing 

gear (MLG) extension problems during 

approach, with the left hand (LH) MLG not 

down. An uneventful landing was made with 

minor damage to the aeroplane and no 

injuries to occupants. 

Subsequent investigation results showed 

that the affected MLG leg shock absorber, P/ 

N D60–3277–10–00, had overextended, 

resulting in the MLG being jammed in the 

gear bay. The overextension had been caused 

by a retaining nut in the MLG shock absorber 

which had loosened itself during operation. 

This condition, if not corrected, could 

inhibit proper extension of the MLG, possibly 

resulting in damage to the aeroplane and 

injury to occupants. 

Prompted by the reported event, Diamond 

Aircraft Industries (DAI) published 

Recommended Service Bulletin (RSB) 42– 

089/RSB 42NG–017 which includes Working 

Instruction (WI) WI–RSB–089/WI–RSB 

42NG–017 (published as a single document) 

to recommend operators to modify the 

affected dampers to P/N D60–3277–10–00_01 

standard, which incorporates installation of a 

new retaining nut and a new seal system for 

the MLG damper that is more durable and 

can withstand a greater temperature range. 

Since that RSB was issued, further analysis 

has shown that the risk of a MLG failing to 

extend is greater than was initially 

determined. Consequently, DAI issued 

Mandatory Service Bulletin MSB 42–095/ 

MSB 42NG–026 to alert aeroplane owners 

and operators accordingly. The new MSB 

contains the same instructions as the earlier 

RSB, but is no longer ‘at owner’s discretion’. 

For the reasons described above, this AD 

requires modification of the affected MLG leg 

shock absorber, P/N D60–3277–10–00. This 

AD also prohibits installation of unmodified 

P/N D60–3277–10–00 MLG leg shock 

absorbers. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

Diamond Aircraft Industries GmbH 

has issued the following service 

information: 

• Mandatory Service Bulletin MSB 

42–095, MSB 42NG–026, dated 

November 11, 2011; 

• Recommended Service Bulletin 

RSB 42–089/1, RSB 42NG–017/1, dated 

April 19, 2011; 

• Page 202 through page 211 of 

CHAPTER 32 LANDING GEAR in 

Diamond Aircraft DA 42 Series AMM, 

Doc # 7.02.01, Rev. 2, dated June 30, 

2008; 

• Page 201 through page 213 in 

Temporary Revision AMM–TR–OA ̈ M 

42–195 of Diamond Aircraft DA 42 

AMM, Doc # 7.02.01, dated July 14, 

2010; and 

• Page 203 through page 214 of 

CHAPTER 32 LANDING GEAR in 

Diamond Aircraft DA 42 NG AMM, Doc 

# 7.02.15, Rev. 1, dated October 15, 

2009. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of the Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

We estimate that this proposed AD 

will affect 175 products of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Required 

parts would cost about $115 per 

product. 

Based on these figures, we estimate 

the cost of the proposed AD on U.S. 

operators to be $49,875, or $285 per 

product. 

According to the manufacturer, some 

of the costs of this proposed AD may be 

covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage for affected individuals. As a 

result, we have included all costs in our 

cost estimate. 

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, 

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 determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 


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Federal Register / Vol. 77, No. 209 / Monday, October 29, 2012 / Proposed Rules 65505 

proposed AD would 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 this proposed 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), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 FAA amends § 39.13 by adding 

the following new AD: 

Diamond Aircraft Industries GmbH: Docket 

No. FAA–2012–1148; Directorate 

Identifier 2012–CE–039–AD. 

(a) Comments Due Date 

We must receive comments by December 

13, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Diamond Aircraft 

Industries GmbH Models DA 42, DA 42 M– 

NG, and DA 42 NG airplanes, all serial 

numbers, certificated in any category. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 32: Landing Gear. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

originated by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as 

overextension of the main landing gear 

(MLG) shock absorber. We are issuing this 

AD to prevent the MLG jamming in the gear 

bay, which could result in damage to the 

aircraft or occupant injury. 

(f) Actions and Compliance 

Unless already done, do the following 

actions: 

(1) Within the next 200 hours time-inservice (TIS) after the effective date of this 

AD or within the next 12 months after the 

effective date of this AD, whichever occurs 

first, modify the left hand (LH) and right 

hand (RH) MLG leg shock absorbers part 

number (P/N) D60–3277–10–00 (no P/N 

change necessary) following Diamond 

Aircraft Industries GmbH Mandatory Service 

Bulletin MSB 42–095, MSB 42NG–026, dated 

November 11, 2011, or replace each MLG leg 

shock absorber P/N D60–3277–10–00 with a 

modified unit P/N D60–3277–10–00–01, 

following, as applicable: Diamond Aircraft 

Industries GmbH Recommended Service 

Bulletin RSB 42–089/1, RSB 42NG–017/1, 

dated April 19, 2011; page 202 through page 

211 of CHAPTER 32 LANDING GEAR in 

Diamond Aircraft DA 42 Series AMM, Doc # 

7.02.01, Rev. 2, dated June 30, 2008; page 201 

through page 213 in Temporary Revision 

AMM–TR–OA ̈ M 42–195 of Diamond Aircraft 

DA 42 AMM, Doc # 7.02.01, dated July 14, 

2010; and page 203 through page 214 of 

CHAPTER 32 LANDING GEAR in Diamond 

Aircraft DA 42 NG AMM, Doc # 7.02.15, Rev. 

1, dated October 15, 2009. 

(2) Modification of an airplane following 

Diamond Aircraft Industries GmbH 

Recommended Service Bulletin RSB 42–089/ 

1, RSB 42NG–017/1, dated April 19, 2011, 

following working instruction WI–MSB 42– 

095, MSB 42NG–026, dated November 11, 

2011, as referenced in Diamond Aircraft 

Industries GmbH Mandatory Service Bulletin 

MSB 42–095, MSB 42NG–026, dated 

November 11, 2011, is acceptable to comply 

with the requirement of paragraph (f)(1) of 

this AD. 

(3) After the effective date of this AD, do 

not install an MLG leg shock absorber P/N 

D60–3277–10–00 on the airplane, unless the 

shock absorber has been modified following 

Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin MSB 42–095, 

MSB 42NG–026, dated November 11, 2011, 

or following Diamond Aircraft Industries 

GmbH Recommended Service Bulletin RSB 

42–089/1, RSB 42NG–017/1, dated April 19, 

2011; and following working instruction WI– 

MSB 42–095, MSB 42NG–026, dated 

November 11, 2011, as referenced in 

Diamond Aircraft Industries GmbH 

Mandatory Service Bulletin MSB 42–095, 

MSB 42NG–026, dated November 11, 2011. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards 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: Mike Kiesov, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4144; fax: (816) 329– 

4090; email: mike.kiesov@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(h) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2012–0174, dated 

September 4, 2012; Diamond Aircraft 

Industries GmbH Mandatory Service Bulletin 

MSB 42–095, MSB 42NG–026, dated 

November 11, 2011; Diamond Aircraft 

Industries GmbH Recommended Service 

Bulletin RSB 42–089/1, RSB 42NG–017/1, 

dated April 19, 2011; page 202 through page 

211 of CHAPTER 32 LANDING GEAR in 

Diamond Aircraft DA 42 Series AMM, Doc # 

7.02.01, Rev. 2, dated June 30, 2008; page 201 

through page 213 in Temporary Revision 

AMM–TR–OA ̈ M 42–195 of Diamond Aircraft 

DA 42 AMM, Doc # 7.02.01, dated July 14, 

2010; and page 203 through page 214 of 

CHAPTER 32 LANDING GEAR in Diamond 

Aircraft DA 42 NG AMM, Doc # 7.02.15, Rev. 

1, dated October 15, 2009, for related 

information. For service information related 

to this AD, contact Diamond Aircraft 

Industries GmbH, N.A. Otto-Stra+e 5, A–2700 

Wiener Neustadt, Austria, telephone: +43 

2622 26700; fax: +43 2622 26780; email: 

office@diamond-air.at; Internet: http:// 

www.diamond-air.at. You may review copies 

of the referenced service information at the 

FAA, Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 


rmajette on DSK2TPTVN1PROD with 
65506 Federal Register / Vol. 77, No. 209 / Monday, October 29, 2012 / Proposed Rules 

Issued in Kansas City, Missouri, on 

October 22, 2012. 

James E. Jackson, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–26499 Filed 10–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1109; Directorate 

Identifier 2011–NM–172–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 757–200 and –200PF 

series airplanes. The existing AD 

currently requires modification of the 

nacelle strut and wing structure, and 

repair of any damage found during the 

modification. Since we issued that AD, 

a compliance time error involving the 

optional threshold formula was 

discovered, which could allow an 

airplane to exceed the acceptable 

compliance time for addressing the 

unsafe condition. This proposed AD 

would specify a maximum compliance 

time limit that overrides the optional 

threshold formula results. We are 

proposing this AD to prevent fatigue 

cracking in primary strut structure and 

consequent reduced structural integrity 

of the strut. 

DATES: We must receive comments on 

this proposed AD by December 13, 

2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

phone: 206–544–5000, extension 1; fax: 

206–766–5680; Internet: https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, Seattle 

Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6440; 

fax: 425–917–6590; email: 

Nancy.Marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–1109; Directorate Identifier 

2011–NM–172–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On August 29, 2003, we issued AD 

2003–18–05, Amendment 39–13296 (68 

FR 53496, September 11, 2003), for 

certain Model 757 series airplanes 

powered by Pratt & Whitney engines. 

That AD requires modification of the 

nacelle strut and wing structure, and 

repair of any damage found during the 

modification. That AD resulted from 

reports indicating that the actual 

operational loads applied to the nacelle 

are higher than the analytical loads that 

were used during the initial design. 

Subsequent analysis and service history, 

which included numerous reports of 

fatigue cracking on certain strut and 

wing structure, indicated that fatigue 

cracking can occur on the primary strut 

structure before an airplane reaches its 

design service objective. We issued that 

AD to prevent fatigue cracking in 

primary strut structure and consequent 

reduced structural integrity of the strut. 

Actions Since Existing AD (68 FR 

53496, September 11, 2003) Was Issued 

Since we issued AD 2003–18–05, 

Amendment 39–13296 (68 FR 53496, 

September 11, 2003), an error in the 

optional threshold formula of the 

compliance time was discovered. If the 

optional threshold formula is used, it 

could result in an unacceptable 

compliance time for addressing the 

unsafe condition. 

Relevant Service Information 

AD 2003–18–05, Amendment 39– 

13296 (68 FR 53496, September 11, 

2003), refers to Boeing Service Bulletin 

757–54–0034, dated May 14, 1998; or 

Revision 1, dated October 11, 2001; as 

the appropriate source of service 

information for modifying the nacelle 

strut and wing structure. Boeing has 

since revised this service bulletin. We 

reviewed Boeing Service Bulletin 757– 

54–0034, Revision 2, dated May 7, 2009. 

This service bulletin specifies a 

compliance time that limits the results 

from the optional threshold compliance 

time formula to within eight years from 

the issuance date of this service 

bulletin. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would retain all 

requirements of AD 2003–18–05, 

Amendment 39–13296 (68 FR 53496, 

September 11, 2003). This proposed AD 

would reduce certain compliance times. 

The optional threshold formula method 

is limited to within eight years after the 

effective date of the AD. This proposed 


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