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9-ANM-116-AMOC-REQUESTS@faa.gov. 

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. 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. 

(m) Related Information 

(1) Refer to MCAI EASA Airworthiness 

Directive 2011–0155, dated August 25, 2011, 

and the following service information, for 

related information. 

(i) Airbus A318/A319/A320/A321 ALS Part 

5—Fuel Airworthiness Limitations, dated 

February 28, 2006. 

(ii) Airbus A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 1, dated December 19, 

2005. 

(iii) A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 2, dated July 8, 2008. 

(iv) Airbus A318/A319/A320/A321 Fuel 

Airworthiness Limitations, Document 

95A.1931/05, Issue 4, dated August 26, 2010. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; Internet 

http://www.airbus.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. 

Issued in Renton, Washington, on May 18, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–13191 Filed 5–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0492; Directorate 

Identifier 2010–NM–126–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (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 747 airplanes. The 

existing AD currently requires repetitive 

visual inspections around the bushings 

of the wing landing gear (WLG) beam 

outboard end fittings for corrosion, and 

rework if necessary; and ultrasonic 

inspections for cracks of the outboard 

end fittings of the WLG support beams, 

and rework if necessary. Since we 

issued that AD, there have been new 

reports of corrosion damage to the end 

fittings of the WLG support beams, and 

one report of subsequent cracking in the 

end fittings. This proposed AD would 

add airplanes and repetitive inspections 

of the outboard end fitting of the left 

and right WLG support beams for cracks 

and corrosion, and corrective actions if 

necessary. We are proposing this AD to 

detect and correct corrosion and 

subsequent cracking in the outboard end 

fittings, which could result in 

separation of the fitting and damage to 

adjacent flight control cables and 

hydraulic systems and consequent 

reduced controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by July 16, 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 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 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6432; 

fax: (425) 917–6590; email: 

bill.ashforth@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–2012–0492; Directorate Identifier 

2010–NM–126–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 July 7, 1989, we issued AD 89–15– 

07, amendment 39–6267 (54 FR 30009, 

July 18, 1989), for certain Model 747 

airplanes. That AD requires visual 

inspections around the bushings of the 

wing landing gear for corrosion, and 

repair if necessary, and ultrasonic 

inspections for cracks of the outboard 

end fittings of the WLG support beams, 

and overhaul if necessary. That AD 

resulted from a report of a fracture of the 

outboard end fitting of a left WLG beam. 

We issued that AD to prevent failure of 

the outboard end fitting of a WLG beam 

with possible damage to control cables 

or hydraulic lines in the area of the 

landing gear beam. 

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Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 32065 

Actions Since Existing AD Was Issued 

Since we issued AD 89–15–07, 

amendment 39–6267 (54 FR 30009, July 

18, 1989), we have received new reports 

of corrosion damage to the end fittings 

of the WLG support beams, and one 

report of subsequent cracking in the end 

fittings. The end fittings are installed on 

the outboard ends of the WLG support 

beams, and they attach to gate fittings 

installed on the rear wing spars. There 

are two types of end fittings used—one 

is a two-piece end fitting installed in a 

‘‘back to back’’ configuration; the other 

is a one-piece end fitting. 

Boeing Service Bulletin 747–57–2244, 

Revision 1, dated July 28, 1988, was 

referred to in the existing AD for 

accomplishing the required actions on 

Model 747 airplanes having line 

numbers 1 through 695. The terminating 

action specified in that service bulletin 

involves replacing each of the end 

fitting lug bore and bolt hole bushings 

with new standard or oversize bushings 

which are installed with sealant to 

provide better corrosion prevention. 

That terminating action was 

incorporated into the design of 

replacement fittings used on production 

airplanes having line numbers 696 and 

subsequent. 

Although the terminating action 

seemed to work well on airplanes 

having line numbers 1 through 695, 

recent reports from operators of 

airplanes having line numbers 696 and 

subsequent revealed that the problem 

occurred again. Further investigation 

revealed that the corrosion started at the 

lug bore and bushing interface because 

moisture continued to develop in that 

area due to exposure of the end fittings 

to environmental conditions. 

Subsequently, cracks have occurred at 

the corroded areas of the end fittings; 

therefore, the terminating action in that 

service bulletin is no longer valid 

because the unsafe condition specified 

in the existing AD has not been 

corrected. 

Relevant Service Information 

Since the issuance of AD 89–15–07, 

amendment 39–6267 (54 FR 30009, July 

18, 1989), Boeing has issued Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. This new service 

information is applicable to Model 747 

airplanes having line numbers 1 through 

1419 inclusive, which includes 

airplanes on which the terminating 

action in AD 89–15–07 was done. 

We have reviewed Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. This service 

bulletin describes procedures for 

repetitive detailed and ultrasonic 

inspections, as applicable, for cracks 

and corrosion of the end fittings of the 

left and right WLG support beams; and 

repetitive detailed inspections of the 

fillet seal for damage, as applicable. The 

service information describes necessary 

actions and options after accomplishing 

the inspections, depending on the 

findings and configurations. Those 

actions and options (including Options 

1A and 1B) include the following: 

• Repairing or changing each end 

fitting (by installing higher interference 

fit bushings on the end fitting), which 

is identified as ‘‘Part 7’’ of this service 

bulletin, may be done in lieu of the 

inspections described previously, but is 

necessary for findings of cracks or 

corrosion. 

• Repetitively inspecting, as 

described previously, along with an 

additional inspection of the fillet seal 

for damage; and applying corrosion 

inhibiting compound or doing ‘‘Part 7’’ 

of this service bulletin, if necessary. 

• Doing ‘‘Post-Part 7 inspections,’’ 

which involves actions similar to the 

inspections for cracks, corrosion, and 

damage described previously. 

The recommended compliance times 

follow: 

• Detailed and ultrasonic inspections: 

The initial compliance time for these 

inspections depends on configuration, 

and is either (1) 8 years on the end 

fitting and 18 months after the date on 

this service bulletin (whichever is later); 

or (2) 10 years on the end fitting and 24 

months after the date on this service 

bulletin (whichever is later). The 

repetitive interval also depends on 

configurations and findings, and ranges 

between 12 and 24 months. 

• ‘‘Part 7’’ of this service bulletin: The 

initial compliance time is the later of 

20,000 total flight cycles on an end 

fitting, and either 18 or 24 months 

(depending on configuration). The 

repetitive interval is either 13,000 or 

16,000 flight cycles on an end fitting; 

depending on configuration. 

• ‘‘Post-Part 7’’ inspections: The 

compliance time is 12 years after the 

repair or change. The subsequent 

repetitive intervals range between 12 

months and 36 months, depending on 

findings and configurations. 

For airplanes on which any crack, 

corrosion, or damage is found, the 

compliance time for ‘‘Part 7’’ or 

application of corrosion inhibitor is 

before further flight. 

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 

certain requirements of the existing AD. 

This proposed AD would also add 

airplanes and require accomplishing the 

actions specified in the service 

information described previously. 

Changes to Existing AD 

We have changed the applicability of 

AD 89–15–07, amendment 39–6267 (54 

FR 30009, July 18, 1989), in this 

proposed AD to identify model 

designations as published in the most 

recent type certificate data sheet for the 

affected models. We have also changed 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

This proposed AD would retain 

certain requirements of AD 89–15–07, 

amendment 39–6267 (54 FR 30009, July 

18, 1989). Since AD 89–15–07 was 

issued, the AD format has been revised, 

and certain paragraphs have been 

rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

89–15–07, Amendment 39–6267 (54 FR 

30009, July 18, 1989) 

Corresponding 

requirement in this 

proposed AD 

paragraph A paragraph (g) 

paragraph B paragraph (g)(1) 

paragraph C paragraph (g)(2) 

paragraph D paragraph (g)(3) 

In addition, we have revised 

paragraph (g)(3) of this proposed AD 

(which was designated as paragraph D. 

in the existing AD) to require that if any 

corrosion is found after the effective 

date of this proposed AD, rework is 

required before further flight. We have 

reduced the compliance time to do the 

rework from ‘‘within 12 months’’ to 

‘‘before further flight’’ because extensive 

service history has shown that the 

deferral of known airplane damage such 

as cracks and corrosion has not 

provided an acceptable level of safety. 

Service history has shown that the 

extent of damage from unrepaired 

corrosion can not reliably be determined 

by inspection techniques. The damaged 

corroded material must first be removed 

and only then can the remaining 

material dimensions be accurately 

compared to the allowable damage 

limits. The extent of unrepaired 

corrosion damage can not be accurately 

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32066 Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 

determined by current inspection 

methods. Further, the reliance for 

operation with known damage is 

predicated on the adjacent and 

associated structure being free from 

other damage during this time period, 

which has not been demonstrated by 

older airplanes. 

Depending on airplane configuration, 

the new proposed inspections would 

take between 1 and 4 work hours per 

airplane, at an average labor rate of $85 

per work hour. Based on these figures, 

the estimated cost of the new 

inspections specified in this proposed 

AD for U.S. operators is between 

$14,705 and $58,820, or between $85 

and $340 per airplane, per inspection 

cycle. 

Difference Between the Proposed AD 

and the Service Information 

Operators should note that Conditions 

6, 13, and 16 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–57A2331, dated November 

12, 2009, specify a detailed inspection. 

However, the corresponding conditions 

in the Accomplishment Instructions of 

this service bulletin specify both 

detailed and high frequency eddy 

current (HFEC) inspections. We have 

confirmed with Boeing that its intent is 

that this service bulletin specify only a 

detailed inspection for those conditions. 

Costs of Compliance 

We estimate that this proposed AD 

affects 173 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspections [retained actions 

from existing AD 89–15–07, 

amendment 39–6267 (54 FR 

30009, July 18, 1989)].

10 work-hours × $85 per hour 

= $850 per inspection cycle.

$0 $850 per inspection cycle ........ $147,050 per inspection 

cycle. 

Inspections [new proposed action].Up to 67 work-hours × $85 per 

hour = $5,695 per inspection 

cycle, depending on configuration.

0 Up to $5,695 per inspection 

cycle, depending on configuration.

Up to $985,235 per inspection cycle, depending on 

configuration. 

We estimate the following costs to do 

any necessary repairs/replacements that 

would be required based on the results 

of the proposed inspection. We have no 

way of determining the number of 

aircraft that might need these repairs/ 

replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair or replacement ........ Up to 71 work-hours × $85 per hour = $6,035, depending on configuration.Up to $26,436, depending 

on configuration.

Up to $32,471, depending 

on configuration. 

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 

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 

removing airworthiness directive (AD) 

89–15–07, Amendment 39–6267 (54 FR 

30009, July 18, 1989), and adding the 

following new AD: 

The Boeing Company: Docket No. FAA– 

2012–0492; Directorate Identifier 2010– 

NM–126–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by July 16, 2012. 

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Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 32067 

(b) Affected ADs 

This AD supersedes AD 89–15–07, 

Amendment 39–6267 (54 FR 30009, July 18, 

1989). 

(c) Applicability 

This AD applies to 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; as identified in Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by new reports of 

corrosion damage to the end fittings of the 

wing landing gear (WLG) support beams, and 

one report of subsequent cracking in the end 

fittings. We are issuing this AD to detect and 

correct corrosion and subsequent cracking in 

the outboard end fittings, which could result 

in separation of the fitting and damage to 

adjacent flight control cables and hydraulic 

systems and consequent reduced 

controllability of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Repetitive Inspections With 

Revised Compliance Times 

This paragraph restates the requirements of 

paragraphs A., B., C., and D., of AD 89–15– 

07, Amendment 39–6267 (54 FR 30009, July 

18, 1989): For airplanes identified in Boeing 

Service Bulletin 747–57–2244, Revision 1, 

dated July 28, 1988: Prior to the 

accumulation of 30,000 flight hours or 8 

years in service, whichever occurs first; or 

within the next 14 months after August 22, 

1989 (the effective date of AD 89–15–07); 

whichever occurs later; visually inspect 

around the fitting lug bushings at the wing 

landing gear (WLG) beam outboard end 

fittings for corrosion, and ultrasonically 

inspect the WLG beam outboard end fittings 

for cracks, in accordance with Boeing Service 

Bulletin 747–57–2244, Revision 1, dated July 

28, 1988. Accomplishing the initial 

inspections required by paragraph (j) of this 

AD terminates the inspections required by 

this paragraph. 

(1) If no cracking or corrosion is found, 

repeat the inspections at intervals not to 

exceed 18 months until paragraph (j) of this 

AD has been accomplished. 

(2) If cracking is found, prior to further 

flight, remove the WLG beam outboard 

fitting, and rework, in accordance with 

Boeing Service Bulletin 747–57–2244, 

Revision 1, dated July 28, 1988. 

(3) If only corrosion is found, within the 

next 12 months, rework in accordance with 

Boeing Service Bulletin 747–57–2244, 

Revision 1, dated July 28, 1988. The 

ultrasonic inspections for cracks required by 

paragraph (g) of this AD must be 

accomplished at intervals not to exceed 6 

months until the rework is accomplished. For 

any corrosion that is found after the effective 

date of this AD, the rework must be done 

before further flight. 

(h) Retained Terminating Action 

This paragraph restates the requirements of 

paragraph E., of AD 89–15–07, Amendment 

39–6267 (54 FR 30009, July 18, 1989): 

Terminating action for the inspections 

required by paragraph (g) of this AD consists 

of rework of the WLG beam outboard fittings, 

in accordance with Boeing Service Bulletin 

747–57–2244, Revision 1, dated July 28, 

1988. 

(i) New Compliance Times for This AD 

For all the actions identified in paragraphs 

(j) through (t) of this AD, do the actions at 

the applicable time specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–57A2331, dated November 12, 

2009. Where paragraph 1.E., ‘‘Compliance’’ of 

this service bulletin specifies a compliance 

time relative to the original issue date of the 

service bulletin, this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(j) New Repetitive Inspections for Groups 1 

Through 5 Airplanes 

For Groups 1 through 3 airplanes, 

Configurations 1 and 2; and Groups 4 and 5 

airplanes: Do detailed and ultrasonic 

inspections of the end fittings for cracks and 

corrosion, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(k) New Inspections for No Crack or 

Corrosion Findings for Groups 1 Through 5 

Airplanes 

If no crack or corrosion is found during any 

inspection required by paragraph (j) of this 

AD, do either of the actions required by 

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

(1) Repeat the detailed and ultrasonic 

inspections of the end fittings for cracks and 

corrosion, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(2) Do a detailed inspection of the end 

fittings for fillet seal damage and for cracks 

and corrosion, in accordance with Part 2 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(i) If no fillet seal damage, crack, or 

corrosion is found: Repeat the inspection 

required by paragraph (k)(2) of this AD. 

(ii) If any fillet seal damage is found, but 

no crack or corrosion is found: Remove the 

fillet seal, and do detailed and HFEC 

inspections of each end fitting for cracks and 

corrosion, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (l) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(1) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, and thereafter repeat the 

inspections required by paragraph 

(k)(2)(ii)(B) of this AD. 

(2) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (l) of this AD. 

(l) New Repair for Crack or Corrosion 

Findings for Groups 1 Through 5 Airplanes 

If any crack or corrosion is found during 

any inspection required by paragraph (j) or 

(k) of this AD: Repair or change the end 

fitting, in accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. After accomplishing the 

repair or change in accordance with Part 7 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2331, dated 

November 12, 2009, do the applicable actions 

required by paragraph (j) of this AD. 

(m) New Repetitive Inspections and 

Corrective Actions for Group 6 Airplanes 

For Group 6 airplanes: Do a detailed 

inspection of the end fittings for fillet seal 

damage and for cracks and corrosion, in 

accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(1) If no fillet seal damage, crack, or 

corrosion is found: Do the detailed 

inspection of the end fittings for fillet seal 

damage and for cracks and corrosion, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(i) If no fillet seal damage, crack, or 

corrosion is found: Repeat the detailed 

inspection required by paragraph (m)(1) of 

this AD. 

(ii) If any fillet seal damage is found, but 

no crack or corrosion is found: Remove the 

fillet seal, and do detailed and HFEC 

inspections of each end fitting for cracks and 

corrosion, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (n) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

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32068 Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 

3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(1) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (n) of this AD. 

(2) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, and thereafter repeat the 

inspections required by paragraph 

(m)(1)(ii)(B) of this AD. 

(2) If any fillet seal damage is found, but 

no crack or corrosion is found: Remove the 

fillet seal, and do detailed and HFEC 

inspections of each end fitting for cracks and 

corrosion, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(i) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (n) of this AD. 

(ii) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (n) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, and thereafter repeat the 

inspections required by paragraph (m)(2)(ii) 

of this AD. 

(n) New Repair for Group 6 Airplanes 

If any crack or corrosion is found during 

any inspection required by paragraph (m) of 

this AD: Repair or change the end fitting, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. After accomplishing the 

repair or change in accordance with Part 7 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2331, dated 

November 12, 2009, do the applicable actions 

required by paragraph (m) of this AD. 

(o) New Optional Terminating Action for 

Part 1, Part 2, and Part 3 Inspections 

In lieu of doing Part 1, Part 2, or Part 3 

inspections required by this AD: Repair or 

change the end fitting, in accordance with 

Part 7 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. After 

accomplishing the repair or change in 

accordance with Part 7 of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, do the applicable actions 

required by paragraphs (p) and (r) of this AD. 

Doing the repair or change terminates the 

Part 1, 2, or 3 inspections for that part only 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(p) New Follow-On End Fitting Inspection 

for Groups 1 Through 5 Airplanes 

For Groups 1 through 5 airplanes on which 

the repair or change specified in Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, has been done: Do 

detailed and ultrasonic inspections of the 

end fittings for cracks and corrosion, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. If no crack or corrosion 

is found, do the actions required by either 

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

(1) Repeat the detailed and ultrasonic 

inspections of the end fittings for cracks and 

corrosion required by paragraph (p) of this 

AD. 

(2) Do a detailed inspection of each end 

fitting for fillet seal damage, cracks, and 

corrosion, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(i) If no fillet seal damage, crack, or 

corrosion is found: Repeat the inspection 

required by paragraph (p)(2) of this AD. 

(ii) If any fillet seal damage is found, but 

no crack or corrosion is found: Remove the 

fillet seal, and do detailed and HFEC 

inspections of each end fitting for cracks and 

corrosion, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, as required 

by paragraph (q) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(1) If any crack or corrosion is found: 

Repair or change the end fitting, as required 

by paragraph (q) of this AD. 

(2) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and repeat the detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(q) New Repair for Groups 1 Through 5 

Airplanes 

If any crack or corrosion is found during 

any inspection required by paragraph (p) of 

this AD: Repair or change the end fitting, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. After accomplishing the 

repair or change in accordance with Part 7 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2331, dated 

November 12, 2009, do the applicable actions 

required by paragraphs (p) of this AD. 

(r) New Follow-On End Fitting Inspection for 

Group 6 Airplanes 

For Group 6 airplanes on which the repair 

or change specified in Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, has been done: Do a 

detailed inspection of the end fittings for 

fillet seal damage, cracks, and corrosion, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(1) If no fillet seal damage, crack, or 

corrosion is found: Do a detailed inspection 

of each end fitting for fillet seal damage, 

cracks, and corrosion, in accordance with 

Part 5 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(i) If no fillet seal damage, crack, or 

corrosion is found: Repeat the inspection 

required by paragraph (r)(1) of this AD. 

(ii) If any fillet seal damage is found, but 

no crack or corrosion is found: Do detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

5 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting as required 

by paragraph (s) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and repeat the detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(1) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(2) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and repeat the detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(2) If any fillet seal damage is found, but 

no crack or corrosion is found: Do detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

4 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 77, No. 105 / Thursday, May 31, 2012 / Proposed Rules 32069 

(i) If any crack or corrosion is found: 

Repair or change the end fitting, as required 

by paragraph (s) of this AD. 

(ii) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, as required 

by paragraph (s) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and repeat the detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(s) New Repair for Group 6 Airplanes 

If any crack or corrosion is found during 

any inspection required by paragraph (r) of 

this AD: Repair or change the end fitting, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(t) New Optional Action for Part 4, Part 5, 

and Part 6 Inspections 

In lieu of doing Part 4, Part 5, or Part 6 

inspections required by this AD: Repair or 

change the end fitting, in accordance with 

Part 7 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. After 

accomplishing the repair or change in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, do the applicable actions 

required by paragraphs (p) and (r) of this AD. 

(u) 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 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 approved for AD 89–15–07, 

Amendment 39–6267 (54 FR 30009, July 18, 

1989), are approved as AMOCs for the 

corresponding requirements of this AD. 

(v) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: (425) 917–6432; fax: (425) 917– 

6590; email: bill.ashforth@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, 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. 

Issued in Renton, Washington, on May 18, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–13187 Filed 5–30–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0495; Directorate 

Identifier 2011–NM–236–AD] 

RIN 2120–AA64 

Airworthiness Directives; Gulfstream 

Aerospace LP (Type Certificate 

Previously Held by Israel Aircraft 

Industries, Ltd.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Gulfstream Aerospace LP (Type 

Certificate previously held by Israel 

Aircraft Industries, Ltd.) Model Galaxy 

and Gulfstream 200 airplanes. This 

proposed AD was prompted by reports 

of degraded brake performance during 

landing due to improperly-sized wear 

indicating pins. This proposed AD 

would require determining the lengths 

of the wear indicating pins of all brake 

assemblies, shortening the pin if the 

wear indicating pin is too long, 

inspecting for normal brake wear, and 

replacing brakes with new brakes if 

necessary. We are proposing this AD to 

detect and correct improperly-sized 

wear indicating pins, which, if not 

corrected, could result in worn-out 

brake pads and subsequent loss of 

braking power, which could result in 

runway overruns. 

DATES: We must receive comments on 

this proposed AD by July 16, 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 between 9 

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

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Gulfstream 

Aerospace Corporation, P.O. Box 2206, 

Mail Station D–25, Savannah, Georgia 

31402–2206; telephone 800–810–4853; 

fax 912–965–3520; email 

pubs@gulfstream.com; Internet http:// 

www.gulfstream.com/product_support/ 

technical_pubs/pubs/index.htm. 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 Operations office 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 Operations 

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: Tom 

Groves, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

mstockstill on DSK4VPTVN1PROD with PROPOSALS