77934 Federal Register / Vol. 76, No. 241 / Thursday, December 15, 2011 / Proposed Rules 

(2) Measurement and Calculation of 

Center Beam Intensity and Beam Angle. 

The test procedure described in ANSI 

C78.379 (incorporated by reference, see 

§ 431.453) shall be followed for 

measuring center beam intensity and 

beam angle of directional lamps with 

symmetrical or asymmetrical beams. For 

lamps with complex beam patterns, the 

test procedure described in ANSI 

C78.379, annex A, shall be followed. 

(3) Test Method for Measuring Lumen 

Maintenance. 

HID lamp lumen maintenance shall be 

determined, following the method 

specified in LM–47 (incorporated by 

reference, see § 431.453), after initial 

lamp aging and initial lumen output 

measurement. At a minimum, the lumen 

maintenance measurements shall be 

collected at 40 percent and 70 percent 

of rated lamp life, as described in LM– 

47. 

(4) Measurement and Calculation of 

Correlated Color Temperature and Color 

Rendering Index. 

HID lamp CCT and CRI shall be 

determined using the methods for 

measurement and characterizing color 

set forth in CIE 15 and CIE 13.3 

(incorporated by reference, see 

§§ 431.453). 

§ 431.455 Energy conservation standards 

and their compliance dates. 

[Reserved] 

[FR Doc. 2011–32162 Filed 12–14–11; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1321; Directorate 

Identifier 2011–NM–045–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Airbus Model A319 series airplanes, 

Model A320–211, –212, –214, –231, 

–232, and –233 airplanes, and Model 

A321 series airplanes that would 

supersede an existing AD. 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: 

Following an automatic [additional center 

tank(s)] ACT fuel transfer failure on an A319, 

it was noted that the ACT manhole cover 

seals were extruded, allowing leakage. 

This condition, if not corrected, can lead 

to fuel and/or vapour leakage, possibly 

resulting in a combustible fuel vapour/air 

mixture in the cargo compartment, which 

would constitute a fire risk. 

* * * * * 

The proposed AD would require 

actions that are intended to address the 

unsafe condition described in the MCAI. 

DATES: We must receive comments on 

this proposed AD by January 30, 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 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. 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

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–2011–1321; Directorate Identifier 

2011–NM–045–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 based on 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 October 26, 2005, we issued AD 

2005–23–02, Amendment 39–14360 (70 

FR 69067, November 14, 2005). That AD 

required actions intended to address an 

unsafe condition on Airbus Model 

A319–100 Series Airplanes, Model 

A320–111 airplanes, Model A320–200 

series airplanes, and Model A321–100 

series airplanes. 

Since we issued AD 2005–23–02, 

Amendment 39–14360 (70 FR 69067, 

November 14, 2005), The European 

Aviation Safety Agency (EASA), which 

is the Technical Agent for the Member 

States of the European Community, has 

issued EASA Airworthiness Directive 

2010–0177, dated August 30, 2010 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Following an automatic ACT fuel transfer 

failure on an A319, it was noted that the ACT 

manhole cover seals were extruded, allowing 

leakage. 

This condition, if not corrected, can lead 

to fuel and/or vapour leakage, possibly 

resulting in a combustible fuel vapour/air 

mixture in the cargo compartment, which 

would constitute a fire risk. 

DGAC France AD F–2004–038 [which 

corresponds to FAA AD 2005–23–02] was 

issued to require the replacement of the ACT 

manhole cover and its seal in accordance 

with SB A320–28–1105, but this 

modification has proved not to be fully 

effective. Therefore, it is necessary to replace 

the seal material and to change the 

installation process in order to prevent such 

seal deformation and possibility of leakage. 


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For the reasons described above, this 

[EASA] AD supersedes DGAC France AD F– 

2004–038 (EASA approval 2004–2110) and 

requires the replacement of the existing 

manhole seal with a new seal. 

This AD also adds certain ACT 

equipped airplanes, produced after AD 

2005–23–02, Amendment 39–14360 (70 

FR 69067, November 14, 2005) was 

issued, to the applicability. This AD 

also removes Model A320–111 airplanes 

from the applicability because there are 

no operational Model A320–111 

airplanes in the United Stated and 

Airbus intends to remove this model 

from the EASA Type Data Sheet. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Mandatory Service 

Bulletin A320–28–1162, Revision 02, 

dated December 18, 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 This 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 the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have proposed 

different actions in this AD from those 

in the MCAI in order to follow FAA 

policies. Any such differences are 

highlighted in a NOTE within the 

proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 721 products of U.S. 

registry. 

The actions that are required by AD 

2005–23–02, Amendment 39–14360 (70 

FR 69067, November 14, 2005) and 

retained in this proposed AD take about 

1 work-hour per product, at an average 

labor rate of $85 per work hour. 

Required parts cost about $0 per 

product. Based on these figures, the 

estimated cost of the currently required 

actions is $85 per product. 

We estimate that it would take about 

3 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these parts. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$183,855, or $255 per product. 

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); and 

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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 Amendment 39–14360 (70 FR 

69067, November 14, 2005) and adding 

the following new AD: 

Airbus: Docket No. FAA–2011–1321; 

Directorate Identifier 2011–NM–045–AD. 

Comments Due Date 

(a) We must receive comments by January 

30, 2012. 

Affected ADs 

(b) This AD supersedes AD 2005–23–02, 

Amendment 39–14360 (70 FR 69067, 

November 14, 2005). 

Applicability 

(c) This AD applies to Airbus airplanes 

listed in paragraphs (c)(1), (c)(2), and (c)(3) of 

this AD; certificated in any category; all serial 

numbers; if equipped with one or more 

additional center tank(s) (ACT) with a part 

number (P/N) listed in table 1 of this AD. 

This AD does not apply to airplanes already 

having received Airbus modification 38036 

in production. 

(1) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(2) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(3) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 


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TABLE 1—AFFECTED ACT PART NUMBERS FOR APPLICABILITY

D2827091100000 D2827105100200 D2827105300600 D2827105500400 

D2827091100200 D2827105100400 D2827105300800 D2827105500600 

D2827091100400 D2827105100600 D2827105400000 D2827105500800 

D2827091100600 D2827105100800 D2827105400200 D2827105600000 

D2827091100800 D2827105200000 D2827105400400 D2827105600200 

D2827091101000 D2827105200200 D2827105400600 D2827105600400 

D2827091300000 D2827105200400 D2827105400800 D2827105600600 

D2827091300200 D2827105200600 D2827105401000 D2827105600800 

D2827091300400 D2827105200800 D2827105401200 D2827107500000 

D2827091300600 D2827105300000 D2827105401400 D2827107500200 

D2827091300800 D2827105300200 D2827105500000 D2827107500400 

D2827105100000 D2827105300400 D2827105500200 D2827107500600 

Subject 

(d) Air Transport Association (ATA) of 

America Code 28: Fuel. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Following an automatic ACT fuel transfer 

failure on an A319, it was noted that the ACT 

manhole cover seals were extruded, allowing 

leakage. 

This condition, if not corrected, can lead 

to fuel and/or vapour leakage, possibly 

resulting in a combustible fuel vapour/air 

mixture in the cargo compartment, which 

would constitute a fire risk. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2005– 

23–02, Amendment 39–14360 (70 FR 69067, 

November 14, 2005), With New Sealing 

Procedures 

(g) Within 30 days (for Model A319–111, 

–112, –113, –114, –115, –131, –132, and –133 

airplanes) or 12 months (for Model A320– 

211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, and 

–131 airplanes) after December 19, 2005 (the 

effective date of AD 2005–23–02, 

Amendment 39–14360 (70 FR 69067, 

November 14, 2005): Determine whether the 

part number (P/N) of each ACT installed on 

the airplane is included in table 2 of this AD. 

If no ACT installed on the airplane has a 

P/N included in table 2 of this AD, no further 

work is required by this paragraph. 

TABLE 2—AFFECTED ACT P/NS FOR AD 2005–23–02, AMENDMENT 39–14360 (70 FR 69067, NOVEMBER 14, 2005) 

D2827091100000 D2827105100200 D2827105300400 D2827105500200 

D2827091100200 D2827105100400 D2827105400000 D2827105500400 

D2827091100600 D2827105200000 D2827105400200 D2827105600000 

D2827091300000 D2827105200200 D2827105400400 D2827105600200 

D2827091300200 D2827105200400 D2827105400600 D2827105600400 

D2827091300400 D2827105300000 D2827105400800 D2827107500000 

D2827105100000 D2827105300200 D2827105500000 D2827107500200 

Manhole Cover/Seal Replacement 

(h) Within 30 days (for Model A319–111, 

–112, –113, –114, –115, –131, –132, and –133 

airplanes) or 12 months (for Model A320– 

211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, and 

–131 airplanes) after December 19, 2005: For 

each ACT P/N listed in table 2 of this AD: 

Before further flight, replace the outer ACT 

manhole cover with a reinforced manhole 

cover and replace the outer manhole cover 

seal with a new seal, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–28–1105, Revision 02, 

dated March 11, 2005. Replacements are also 

acceptable if done before December 19, 2005, 

in accordance with Airbus Service Bulletin 

A320–28–1105, Revision 01, dated March 18, 

2003; and Airbus Service Bulletin A320–28– 

1105, dated October 22, 2002. As of the 

effective date of this AD, doing the manhole 

cover seal replacement required by paragraph 

(i) of this AD, terminates the manhole cover 

seal replacement required by this paragraph. 

New Requirements of This AD 

ACT Modification 

(i) Within 3,000 flight cycles or 24 months, 

whichever occurs first after the effective date 

of this AD: Modify the affected ACT listed in 

table 1 of this AD by replacing the manhole 

seal, in accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–28–1162, Revision 02, dated 

December 18, 2009. Accomplishing the 

manhole cover sealing replacement specified 

in this paragraph terminates the manhole 

cover sealing replacement required in 

paragraph (h) of this AD. 

Parts Installation 

(j) As of the effective date of this AD, no 

person may install an ACT, whose part 

number is listed in table 1 of this AD, on any 

airplane unless it has been modified prior to 

its installation, in accordance with Airbus 

Mandatory Service Bulletin A320–28–1162, 

Revision 02, dated December 18, 2009. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(k) Modifying the ACT in accordance with 

Airbus Mandatory Service Bulletin A320–28– 

1162, dated February 6, 2008; or Revision 01, 

dated July 16, 2008; before the effective date 

of this AD is acceptable for compliance with 

the corresponding modification required by 

paragraph (i) of this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(l) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 

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/ 


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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. 

Related Information 

(m) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0177, dated August 30, 2010; 

Airbus Mandatory Service Bulletin A320–28– 

1162, Revision 02, dated December 18, 2009; 

and Airbus Service Bulletin A320–28–1105, 

Revision 02, dated March 11, 2005; for 

related information. 

Issued in Renton, Washington, on 

December 6, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–32076 Filed 12–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1320; Directorate 

Identifier 2011–NM–208–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 adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 777 airplanes. 

This proposed AD was prompted by 

four reports of retaining cross bolt 

hardware not fully engaged into the fuse 

pins of the forward trunnion lower 

housing of the main landing gear (MLG), 

which could result in an incorrect MLG 

emergency landing break-away 

sequence. This proposed AD would 

require a detailed inspection of the fuse 

pin cross bolts and fuse pins of the left 

and right MLG forward trunnion lower 

housing to verify that the cross bolts are 

correctly installed and that there are no 

missing fuse pins, and replacement of 

the fuse pins if necessary. We are 

proposing this AD to prevent an 

incorrect emergency landing MLG 

break-away sequence, which could 

result in puncturing of the wing box and 

consequent fuel leaks and an airplane 

fire. Failure of the fuse pins could also 

result in a premature landing gear 

collapse causing a runway excursion 

during take-off or landing. 

DATES: We must receive comments on 

this proposed AD by January 30, 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, Washington 98124– 

2207; phone: (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 

(phone: (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

James Sutherland, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

Washington 98057–3356; phone: (425) 

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

James.Sutherland@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2011–1320; Directorate Identifier 2011– 

NM–208–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 

We have received four reports of 

retaining cross bolt hardware not fully 

engaged into the fuse pins of the MLG 

forward trunnion lower housing. 

Reports indicated the incorrectly 

installed cross bolts were found during 

a scheduled C-check inspection, an 

MLG replacement, a 4C inspection, and 

a hard landing inspection. All findings 

indicated that the cross bolt and lock 

wire were intact, but the cross bolt had 

not properly engaged in the fuse pin. 

The cross bolt and lock wire are used to 

prevent the fuse pin from migrating out 

of position. A migrated or missing fuse 

pin in the MLG forward trunnion lower 

housing can cause the remaining fuse 

pins in the MLG forward trunnion 

upper and lower housing to wear at a 

faster rate and also result in possible 

failure of the adjacent fuse pins in the 

MLG forward trunnion upper and lower 

housing. Failure of the fuse pins in the 

MLG forward trunnion upper and lower 

housing could result in an incorrect 

emergency landing MLG break-away 

sequence, which will cause the MLG to 

puncture the wing box and consequent 

fuel leaks and possible airplane fire. 

Failure of the fuse pins could also result 

in a premature landing gear collapse 

causing a runway excursion during takeoff or landing. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 777–57A0090, dated August 24, 

2011. This service information describes 

procedures for doing a detailed 

inspection of the fuse pin cross bolts 

and fuse pins of the left and right MLG 

forward trunnion lower housing to 

verify that the cross bolts are correctly 


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