21426 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations 

(k) Parts Installation 

As of the effective date of this AD, do not 

install any No. 2 or No. 3 window having P/ 

N 65B27042–( ), 65B27043–( ), 65B27046– 

( ), or 65B27047–( ) that is not new or on 

which the window flight hours are not 

known, on any airplanes, unless the actions 

specified in paragraph (g) of this AD are 

done. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(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. 

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) 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. 

(4) AMOCs previously approved in 

accordance with AD 2007–15–10, 

Amendment 39–15139 (72 FR 41438, July 30, 

2007; as corrected by 72 FR 53923, 

September 21, 2007), are approved as 

AMOCs for the corresponding provisions of 

this AD except previous AMOCs approving 

window replacement that do not specify 

installing dual structural glass pane windows 

are not considered approved for 

corresponding inspection methods required 

by this AD. 

(m) Related Information 

For more information about this AD, 

contact Nathan P. Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

Seattle Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6428; fax: 425–917–6590; email: 

Nathan.P.Weigand@faa.gov. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) under 5 U.S.C. 552(a) and 1 CFR part 

51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on May 15, 2012. 

(i) Boeing Service Bulletin 747–56A2012, 

Revision 1, dated August 12, 2010. 

(4) The following service information was 

approved for IBR on September 4, 2007 (72 

FR 41438, July 30, 2007; as corrected by 72 

FR 53923, September 21, 2007). 

(i) Boeing Alert Service Bulletin 747– 

56A2012, dated August 24, 2006. 

(5) 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; phone: 

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

5680; email: me.boecom@boeing.com; 

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

(6) You may review copies of the 

referenced 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. 

(7) 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 an NARA facility, 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 January 

23, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–8452 Filed 4–9–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0915; Directorate 

Identifier 2011–NM–020–AD; Amendment 

39–17013; AD 2012–07–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 747 airplanes. 

This AD was prompted by reports of 

fractured latch pins found in service; 

investigation revealed that the cracking 

and subsequent fracture were initiated 

by fatigue and propagated by a 

combination of fatigue and stress 

corrosion. This AD requires repetitive 

general visual inspections for broken or 

missing latch pins of the lower sills of 

the forward and aft lower lobe cargo 

doors; repetitive detailed inspections for 

cracking of the latch pins; and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

fractured or broken latch pins, which 

could result in a forward or aft lower 

lobe cargo door opening and detaching 

during flight, and consequent rapid 

decompression of the airplane. 

DATES: This AD is effective May 15, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 15, 2012. 

ADDRESSES: 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; email 

me.boecom@boeing.com; 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, Washington. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Nathan Weigand, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6428; fax: (425) 917–6590; email: 

nathan.p.weigand@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on September 1, 2011 (76 FR 

54405). That NPRM proposed to require 

repetitive general visual inspections for 

broken or missing latch pins of the 

lower sills of the forward and aft lower 

lobe cargo doors; repetitive detailed 

inspections for cracking of the latch 

pins; and corrective actions if necessary. 


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Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations 21427 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request to Withdraw the NPRM (76 FR 

54405, September 1, 2011) 

United Parcel Service (UPS) asked 

that we withdraw the NPRM (76 FR 

54405, September 1, 2011). UPS stated 

that there is a lack of justification for 

issuing the NPRM and added that it is 

being issued based on a report of a 

fatigue crack in the 17–4PH material 

latch pins of the lower cargo door, and 

the assumption that adjacent latch pins 

could also be affected. UPS noted that 

the latching structures of the lower 

forward and aft cargo door each include 

eight latch pins; those latch pins are 

part of a fail-safe design, which should 

preclude critical failure with the failure 

of one element. UPS added that the 

Model 747–400 maintenance planning 

document includes a detailed 

inspection of the latch mechanism of 

the lower cargo door, which includes 

the latch pins, at 2 year or 2,000 flight 

cycle intervals, whichever occurs first. 

UPS noted that the NPRM would 

require repetitive inspections at 1,600- 

flight-cycle intervals—a modest increase 

in frequency over the existing 

maintenance program—which has 

already been proven successful at 

detecting damage to adjacent latch pins. 

UPS concluded that, based on the 

extensive fleet history of the latch pins 

of these lower cargo doors, with no 

reports of adjacent pin failures, the 

existing maintenance program 

inspections of the latch pins are 

adequate. 

We do not agree with the commenter’s 

request to withdraw the NPRM (76 FR 

54405, September 1, 2011). Although 

the commenter has not experienced pin 

failure in service, the manufacturer has 

found pin fatigue failure on another 

airplane of the same type design. 

Therefore, we find we must issue this 

AD to address the identified unsafe 

condition on the entire fleet. 

The inspections identified in the 

maintenance planning document are 

general visual inspections of the entire 

door. The inspections required by this 

final rule include detailed inspections 

of the latch pins themselves. These 

detailed inspections are the result of the 

pin fracturing in service. The fractured 

pin was the number eight latch pin on 

the lower sill of the aft lower lobe cargo 

door; investigation by the manufacturer 

revealed that the crack initiated due to 

fatigue, and propagated by a 

combination of fatigue and stress 

corrosion. If the latch pins on the lower 

sill are not regularly inspected, and 

broken latch pins are not replaced, the 

forward and/or aft cargo door could 

open during service, resulting in loss of 

the cargo door, rapid decompression, 

and significant damage to the airplane. 

No change to the AD is necessary in this 

regard. 

Request To Clarify Language in 

Relevant Service Information Section 

Boeing asked that the description 

specified in the ‘‘Relevant Service 

Information’’ section of the NPRM (76 

FR 54405, September 1, 2011) be 

changed as follows: ‘‘The service 

bulletin describes procedures for 

repetitive detail inspections of latch 

pins for broken or missing latch pins of 

the lower sills of the forward and aft 

lower lobe cargo doors; repetitive 

detailed inspections of the replaced 

latch pins for cracked, broken or 

missing latch pins; and corrective 

actions if necessary.’’ Boeing stated that 

Boeing Alert Service Bulletin 747– 

53A2835, dated October 28, 2010, 

necessitates that a detailed inspection 

be done on all pins (including 

previously replaced pins). Boeing added 

that the detailed inspection is for cracks, 

and the general visual inspection is to 

look for the broken and missing pins. 

Boeing notes that paragraph (g) of the 

NPRM provides the correct description 

of the inspections specified in the 

service bulletin. 

We acknowledge the commenter’s 

concern and agree that the language 

could be clarified somewhat; however, 

since that section of the preamble does 

not reappear in the final rule, no change 

to this AD is necessary in this regard. 

Request To Include Revision 1 of the 

Referenced Service Bulletin 

Boeing also asked that Boeing Alert 

Service Bulletin 747–53A2835, Revision 

1, dated December 8, 2011, be included 

in the NPRM (76 FR 54405, September 

1, 2011) for accomplishing certain 

actions. Boeing Alert Service Bulletin 

747–53A2835, dated October 28, 2010, 

was referred to as the appropriate source 

of service information for accomplishing 

the actions specified in the NPRM. 

Boeing added that Boeing Alert Service 

Bulletin 747–53A2835, Revision 1, 

dated December 8, 2011, is scheduled 

for FAA-approval, and includes a latch 

pin modification and post-modification 

inspection to address the safety issue. 

We have reviewed Boeing Alert 

Service Bulletin 747–53A2835, Revision 

1, dated December 8, 2011, and agree to 

include it in this final rule as an 

additional source of service information. 

Boeing Alert Service Bulletin 747– 

53A2835, Revision 1, dated December 8, 

2011, reduces an existing compliance 

time, adds a latch pin modification, and 

repetitive post-modification inspections. 

We are including the actions in Boeing 

Alert Service Bulletin 747–53A2835, 

Revision 1, dated December 8, 2011, as 

optional in order to avoid delaying 

issuance of the AD. We have revised 

paragraph (g) of this AD accordingly. 

We are currently considering additional 

rulemaking to require the modification 

and post-modification inspections. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

54405, September 1, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 54405, 

September 1, 2011). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Costs of Compliance 

We estimate that this AD affects 228 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection ...... 3 work-hours × $85 per hour = $255 per inspection cycle.$0 $255 per inspection cycle ..... $58,140 per inspection cycle. 


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21428 Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations 

We estimate the following costs to do 

any necessary replacements/ 

modifications that would be required 

based on the results of the required 

inspection. We have no way of 

determining the number of aircraft that 

might need these actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Replacement of latch pins .................. 8 work-hours × $85 per hour = $680 ............................................................. $0 $680 

Modification of latch fittings ................ 36 hours × $85 per work-hours = $3,060 ...................................................... 0 3,060 

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 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 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 airworthiness 

directive (AD): 

2012–07–07 The Boeing Company: 

Amendment 39–17013; Docket No. 

FAA–2011–0915; Directorate Identifier 

2011–NM–020–AD. 

(a) Effective Date 

This AD is effective May 15, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747–400F, 

747SR, and 747SP series airplanes; 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53: Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fractured latch pins found in service; 

investigation revealed that the cracking and 

subsequent fracture were initiated by fatigue 

and propagated by a combination of fatigue 

and stress corrosion. We are issuing this AD 

to detect and correct fractured or broken 

latch pins, which could result in a forward 

or aft lower lobe cargo door opening and 

detaching during flight, and consequent 

rapid decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

Before the accumulation of 6,000 total 

flight cycles, or within 1,000 flight cycles 

after the effective date of this AD, whichever 

occurs later: Do a general visual inspection 

for broken or missing latch pins of the lower 

sills of the forward and aft lower lobe cargo 

doors, and a detailed inspection for cracking 

of the latch pins, in accordance with 

paragraph 3.B., ‘‘Work Instructions,’’ of 

Boeing Alert Service Bulletin 747–53A2835, 

dated October 28, 2010; or Boeing Alert 

Service Bulletin 747–53A2835, Revision 1, 

dated December 8, 2011. Repeat the 

inspections thereafter at the applicable 

intervals specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2835, dated October 28, 

2010; or Boeing Alert Service Bulletin 747– 

53A2835, Revision 1, dated December 8, 

2011. Before further flight, do all applicable 

corrective actions, in accordance with 

paragraph 3.B., ‘‘Work Instructions,’’ of 

Boeing Alert Service Bulletin 747–53A2835, 

dated October 28, 2010; or Boeing Alert 

Service Bulletin 747–53A2835, Revision 1, 

dated December 8, 2011. 

(h) Special Flight Permits 

Special flight permits may be issued in 

accordance with sections 21.197 and 21.199 

of the Federal Aviation Regulations (14 CFR 

21.197 and 21.199) to operate the airplane to 

a location where the airplane can be 

modified (if the operator elects to do so), 

provided the cabin is not pressurized. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

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) 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 ODA that has 

been authorized by the Manager, Seattle 


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Federal Register / Vol. 77, No. 69 / Tuesday, April 10, 2012 / Rules and Regulations 21429 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane. 

(j) Related Information 

For more information about this AD, 

contact Nathan Weigand, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6428; fax: 

(425) 917–6590; email: 

nathan.p.weigand@faa.gov. 

(k) Material Incorporated by Reference 

You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

U.S.C. 552(a) and 1 CFR part 51 of the 

following service information. 

(1) Boeing Alert Service Bulletin 747– 

53A2835, dated October 28, 2010. 

(2) Boeing Alert Service Bulletin 747– 

53A2835, Revision 1, dated December 8, 

2011. 

(3) 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; 

email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

(4) You may review copies of the 

referenced 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. 

(5) 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/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on March 

28, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–8232 Filed 4–9–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0025; Directorate 

Identifier 2010–NM–208–AD; Amendment 

39–17012; AD 2012–07–06] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777 

airplanes. This AD was prompted by a 

new revision to the airworthiness 

limitations of the maintenance planning 

document. This AD requires revising the 

maintenance program to update 

inspection requirements to detect 

fatigue cracking of principal structural 

elements (PSEs). We are issuing this AD 

to ensure that fatigue cracking of various 

PSEs is detected and corrected; such 

fatigue cracking could adversely affect 

the structural integrity of these 

airplanes. 

DATES: This AD is effective May 15, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 15, 2012. 

ADDRESSES: 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; email 

me.boecom@boeing.com; 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, Washington. 

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 AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

James Sutherland, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6533; fax: (425) 917–6590; email: 

James.Sutherland@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on January 19, 2011 (76 FR 

3054). That NPRM proposed to require 

revising the maintenance program to 

update inspection requirements to 

detect fatigue cracking of principal 

structural elements (PSEs). 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 3054, 

January 19, 2011) and the FAA’s 

response to each comment. 

Request To Refer to Latest Service 

Information 

Boeing and Japan Airlines (JAL) 

requested that we revise the NPRM (76 

FR 3054, January 19, 2011) to refer to 

two new revisions of Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ D622W001–9, of the Boeing 

777 Maintenance Planning Data (MPD) 

Document, published after we issued 

the NPRM. Boeing stated that both 

revisions contain the same structures 

airworthiness limitations (AWL) data, 

but were revised for reasons that did not 

affect the data in Subsection B, 

Airworthiness Limitations—Structural 

Inspections of that document, which 

was specified in the NPRM. 

We agree with the request to refer to 

the later service information. We have 

changed this final rule to refer to 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ D622W001–9, 

Revision July 2011, of the Boeing 777 

Maintenance Planning Data (MPD) 

Document to this AD. (Section 9, 

‘‘Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs),’’ D622W001–9, Revision 

January 2010, of the Boeing 777 

Maintenance Planning Data (MPD) 

Document was specified in the NPRM 

(76 FR 3054, January 19, 2011).) 

(Subsection B, Airworthiness 

Limitations—Structural Inspections, of 

Section 9, ‘‘Airworthiness Limitations 

(AWLs) and Certification Maintenance 

Requirements (CMRs),’’ D622W001–9, 

of the Boeing 777 Maintenance Planning 

Data (MPD) Document is identical to the 

January 2010 revision.) We have 

changed paragraph (g) in this final rule 

accordingly. 


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