81424 Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 

(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): 

2010–26–08 The Boeing Company: 

Amendment 39–16547; Docket No. 

FAA–2010–0127; Directorate Identifier 

2009–NM–242–AD. 

Effective Date 

(a) This AD is effective February 1, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

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

–400ER series airplanes, certificated in any 

category; as identified in Boeing Service 

Bulletin 767–25–0477, dated August 27, 

2009. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 25: Equipment/Furnishings. 

Unsafe Condition 

(e) This AD results from reports of fault 

messages caused by an improperly crimped 

hinge pins on the movable ceiling panel of 

the entryway door on the forward left side 

coming into contact with wires and causing 

damage. The Federal Aviation 

Administration is issuing this AD to detect 

and correct improperly crimped hinge pins, 

which could damage tie rods and wire 

bundles, causing shorts in many systems, 

including the spar fuel shut-off valve, oxygen 

mask deployment, and burned wires, which 

could be an ignition source in a hidden area 

of the airplane. 

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. 

Inspections and Corrective Actions 

(g) Within 72 months after the effective 

date of this AD: Accomplish the inspections 

required by paragraphs (g)(1), (g)(2), (g)(3), 

and (g)(4) of this AD, and do all applicable 

corrective actions and part marking, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

25–0477, dated August 27, 2009. If, during 

the following inspections, any pin migration, 

improper crimping, tie-rod damage, or wire 

damage is found, do all applicable corrective 

actions, in accordance with Boeing Service 

Bulletin 767–25–0477, dated August 27, 

2009, before further flight. 

(1) A detailed inspection for pin migration 

at either end of the hinge assembly and to 

detect damage to the pin. 

(2) A detailed inspection for correct crimp 

at both ends and to detect damage to hinge 

stock. 

(3) A detailed inspection of the ceiling area 

for any visible cosmetic and tie-rod chafing 

that could be caused by a migrated hinge pin. 

(4) A detailed inspection for wire damage 

and breakage. 

Alternative Methods of Compliance 

(AMOCs) 

(h)(1) The Manager, Seattle Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Stephen Styskal, 

Aerospace Engineer, Cabin Safety and 

Environmental Systems Branch, ANM–150S, 

FAA, Seattle Aircraft Certification Office 

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

Washington 98057–3356; telephone (425) 

917–6439; fax (425) 917–6590. Or, e-mail 

information to 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Related Information 

(i) For more information about this AD, 

contact Stephen Styskal, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office (ACO), 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6439; fax (425) 

917–6590. 

Material Incorporated by Reference 

(j) You must use Boeing Service Bulletin 

767–25–0477, dated August 27, 2009, to do 

the actions required by this AD, unless the 

AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

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

Internet https://www.myboeingfleet.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at 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 

December 13, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–31967 Filed 12–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1250; Directorate 

Identifier 2010–SW–075–AD; Amendment 

39–16548; AD 2010–26–09] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) Model 

S76A, B, and C Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing emergency airworthiness 

directive (EAD) for the specified 

Sikorsky model helicopters. The EAD 

requires inspecting the LITEF Attitude 

Heading and Reference System (AHRS) 

unit of the navigation system to 

determine if it is at a Mod Status ‘‘18.’’ 

If either AHRS unit is at Mod Status 

‘‘18,’’ the EAD requires installing 

placards on the instrument panel to 

prohibit single pilot instrument flight 

rule (IFR) and single pilot night flight 

and reducing airspeeds to 120 knots 

indicated airspeed (KIAS) if both 

autopilots uncouple during instrument 

meteorological conditions (IMC) or 

night flight. The EAD also requires 

inserting minimum crew and airspeed 

limitations into the Limitations section 

of the applicable Rotorcraft Flight 

Manual (RFM) to limit the minimum 


srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 81425 

flight crew to 2 pilots for night flight 

and IFR flight and to reduce airspeed to 

120 KIAS if both autopilots uncouple 

during IMC or night flight. This 

amendment contains the same 

requirements but draws the appropriate 

distinctions between IFR and IMC as 

used in the intended operating 

limitations. Also, unlike the EAD, this 

AD states the airspeed must be reduced 

to 120 KIAS if both autopilots uncouple 

during IMC or night flight. Further, we 

are removing the limitation contained in 

the Active Temporary Revisions relating 

to pilots keeping their hands and feet 

near the flight controls. This AD was 

prompted by the need to supersede the 

EAD to state the distinction between IFR 

and IMC as used in the operating 

limitations and to reduce the airspeed to 

120 KIAS if both autopilots uncouple 

during IMC or night flight. The actions 

specified by this AD are intended to 

implement operating limitations based 

on an anomaly in the AHRS related to 

the 26 volt AC inverter that could result 

in a decoupling of both autopilots and 

to prevent loss of control of the 

helicopter during IMC and during night 

flight. 

DATES: Effective January 12, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of January 12, 

2011. 

We must receive comments on this 

AD by February 28, 2011. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• 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. 

You may get the service information 

identified in this AD from Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT, telephone (203) 383–4866, 

e-mail address tsslibrary@sikorsky.com, 

or at http://www.sikorsky.com. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information 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 Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Tony Pigott, Aviation Safety Engineer, 

Boston Aircraft Certification Office, 12 

New England Executive Park, 

Burlington, MA 01803, telephone (781) 

238–7158, fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: On May 

19, 2010, we issued EAD No. 2010–11– 

52, to require inspecting the AHRS unit 

to determine if it is at a Mod Status ‘‘18.’’ 

If the nameplate indicates that either 

AHRS unit is a Mod Status ‘‘18,’’ the 

EAD requires installing placards on the 

instrument panel to prohibit single pilot 

IFR and single pilot night flight and 

reducing airspeeds to 120 KIAS if both 

autopilots uncouple during IMC or night 

flight. The EAD also requires inserting 

the Active Temporary Revision listed in 

Table 1 into the Limitations section of 

the RFM to limit the minimum flight 

crew to 2 pilots for IFR and night flight. 

That action was prompted by reports of 

intermittent malfunctions of the LITEF 

AHRS units of the navigation system. 

The EAD states that the condition, if not 

corrected, could result in malfunction of 

the autopilots, inability to reset the 

autopilots, an uncommanded roll, 

reduction in rotorcraft functional 

capabilities, inability of the crew to 

perform the required tasks, and 

subsequent loss of control of the 

helicopter. 

Since issuing EAD 2010–11–52, we 

have discovered that we did not draw 

the appropriate distinctions between 

IFR and IMC as used in the intended 

operating limitations, and we did not 

state the requirement to reduce the 

airspeed to 120 KIAS if both autopilots 

uncouple during IMC or night flight. 

Further, we did not intend to adopt as 

a limitation the provision contained in 

the Active Temporary Revisions relating 

to pilots keeping their hands and feet 

near the flight controls as this is 

considered normal conduct of a 

helicopter pilot exercising good care 

and sound judgment regardless of the 

AHRS unit installed. 

We have reviewed Sikorsky Alert 

Service Bulletin No. 76–34–11, dated 

May 17, 2010 (ASB). The ASB specifies 

informing operators of an interim 

minimum flight crew restriction of two 

pilots for IFR and night flight for 

helicopters equipped with LITEF LCR– 

100, Mod Status ‘‘18,’’ AHRS units. The 

ASB also specifies removing and 

inspecting the AHRS units to determine 

if part number (P/N) 145130–7100, Mod 

Status ‘‘18,’’ is installed, and if it is 

installed, identifying the unit with a 

placard with a different P/N. Finally, 

the ASB specifies installing 2 placards, 

P/N SS9140–1746, or locally fabricated 

placards, one on each side of the 

instrument panel. 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other Sikorsky model 

helicopters of these same type designs, 

this AD supersedes EAD 2010–11–52 by 

retaining the current requirements but 

by clarifying the appropriate 

distinctions between IFR and IMC as 

used in the intended operating 

limitations. Also, in this AD we state the 

requirement to reduce the airspeed to 

120 KIAS if both autopilots uncouple 

during IMC or night flight. Further, we 

have removed the Active Temporary 

Revisions to correct the provision 

relating to pilots keeping their hands 

and feet near the flight controls. In the 

place of the Active Temporary 

Revisions, we are now requiring you to 

insert a copy of this AD into the 

Limitations section of the applicable 

RFM to address the airspeed limitations 

and the minimum flight crew. 

Accomplish the actions in this AD by 

following specified portions of the ASB 

described previously. This AD does not 

require installing placards containing 

the Sikorsky P/N 76070–60019–101 on 

the AHRS unit as specified in the 

Sikorsky ASB. Also, this AD revises the 

unsafe condition statement by stating 

that the actions are intended to 

implement operating limitations based 

on an anomaly in the AHRS related to 

the 26 volt AC inverter that could result 

in a decoupling of both autopilots and 

to prevent loss of control of the 

helicopter during IMC and night flight. 

The short compliance time involved 

is required because the previously 

described critical unsafe condition can 

adversely affect the controllability of the 

helicopter. Therefore, determining if the 

AHRS unit is an affected unit, installing 

certain placards on the instrument 

panel, and inserting limitations into the 

Limitations section of the applicable 

RFM are required within 5 days, and 

this AD must be issued immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 


srobinson on DSKHWCL6B1PROD with RULES
81426 Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 

We estimate that this AD will affect 

1 helicopter in the U.S. registry. We 

estimate it will take about 1 work hour 

to inspect the AHRS unit to determine 

if it is a Mod Status ‘‘18,’’ 1 work hour 

to fabricate and install a placard, and 

1⁄2 work hour to revise the RFM. The 

average labor rate is $85 per hour and 

there are only minimal parts costs. 

Based on these figures, the total cost 

impact of this AD on U.S. operators is 

$213. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and an 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments regarding this 

AD. Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2010–1250; 

Directorate Identifier 2010–SW–075– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light 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 

concerning this AD. Using the search 

function of the docket Web site, you can 

find and read the comments to any of 

our dockets, including the name of the 

individual who sent the comment. You 

may review the DOT’s complete Privacy 

Act Statement in the Federal Register 

published on April 11, 2000 (65 FR 

19477–78). 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

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

3. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD. See the AD docket to examine 

the economic evaluation. 

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. 

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 

a new AD to read as follows: 

2010–26–09 Sikorsky Aircraft Corporation: 

Amendment 39–16548; Docket No. 

FAA–2010–1250; Directorate Identifier 

2010–SW–075–AD. Supersedes EAD 

2010–11–52; Directorate Identifier 2010– 

SW–059–AD. 

Applicability: Model S–76A, B, and C 

helicopters, with LITEF LCR–100, Attitude 

Heading and Reference System (AHRS) Unit, 

part number (P/N) 145130–7100, installed, 

certificated in any category. 

Compliance: Within 5 days, unless 

accomplished previously, and any time 

thereafter when installing a LITEF LCR–100, 

AHRS Unit, P/N 145130–7100. 

To implement operating limitations based 

on an anomaly in the AHRS related to the 26- 

volt AC inverter that could result in a 

decoupling of both autopilots and to prevent 

loss of the helicopter during instrument 

meteorological conditions (IMC) and while 

operating under instrument flight rules (IFR) 

and night flight, do the following: 

(a) By referencing the nameplate of the No. 

1 and No. 2 AHRS unit, determine whether 

the modification (Mod) status is at ‘‘18.’’ If the 

Mod status is ‘‘18’’ for either AHRS unit: 

(1) Install instrument panel placards as 

shown in Figure 2 in the areas depicted in 

Figure 3 of Sikorsky Alert Service Bulletin 

No. 76–34–11, dated May 17, 2010 (ASB), 

and by following the Accomplishment 

Instructions, paragraph 3.A.(6)(c) through (d) 

of the ASB. 

(2) Revise the ‘‘Minimum Flight Crew’’ 

section of the Operating Limitations section 

of the Rotorcraft Flight Manual (RFM) as 

follows: ‘‘For helicopters with an LCR–100 

Mod Status ‘18’ AHRS installed, two pilots 

are required for IFR and night flights.’’ 

(3) Revise the ‘‘Airspeed Limits’’ section of 

the Operating Limitations section of the RFM 

as follows: ‘‘For helicopters with an LCR–100 

Mod Status ‘18’ AHRS installed, airspeed is 

limited to 120 knots indicated airspeed 

(KIAS) when both autopilots are uncoupled 

and operating at night or in IMC.’’ 

(4) When present, remove and discard the 

following Active Temporary Revisions from 

the Operating Limitations section of the RFM 

for each affected helicopter: 

TABLE 1 

Model RFM document No. Active temporary rev. 

No. 

S–76A ........................................................................................................................................... SA–4047–76–1 ........... T–Revision 3. 

S–76B ........................................................................................................................................... SA 4047–76B–1 .......... T–Revision 3. 

S–76C (TurboMeca Arriel 1S1 engines installed) ........................................................................ SA 4047–76C–1 ......... T–Revision 3. 

S–76C (TurboMeca Arriel 2S1 engines installed) ........................................................................ SA 4047–76C–10 ....... T–Revision 4. 

S–76C (TurboMeca Arriel 2S1 engines installed and s/n 760511 and subsequent) .................. SA 4047–76C–14 ....... T–Revision 4. 

S–76C (TurboMeca Arriel 2S2 engines installed) ........................................................................ SA 4047–76C–15 ....... T–Revision 1. 


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Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 81427 

(5) Revise the Operating Limitations 

section of the RFM by inserting a copy of this 

AD into the appropriate section of the RFM. 

(b) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Boston Aircraft 

Certification Office, FAA, Attn: Tony Pigott, 

Aviation Safety Engineer, 12 New England 

Executive Park, Burlington, MA 01803, 

telephone (781) 238–7158, fax (781) 238– 

7170. 

(c) The Joint Aircraft System/Component 

(JASC) Code is 3420: Navigation. 

(d) Installing the placards shall be done by 

following the specified portions of Sikorsky 

Alert Service Bulletin No. 76–34–11, dated 

May 17, 2010. The Director of the Federal 

Register approved this incorporation by 

reference in accordance with 5 U.S.C. 552(a) 

and 1 CFR part 51. Copies may be obtained 

from Sikorsky Aircraft Corporation, Attn: 

Manager, Commercial Technical Support, 

mailstop s581a, 6900 Main Street, Stratford, 

CT, telephone (203) 383–4866, e-mail address 

tsslibrary@sikorsky.com, or at http://www.

sikorsky.com. Copies may be inspected at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas, or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://www.archives.

gov/federal_register/code_of_federal_

regulations/ibr_locations.html. 

(e) This amendment becomes effective on 

January 12, 2011. 

Issued in Fort Worth, Texas, on December 

13, 2010. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–31962 Filed 12–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0232; Directorate 

Identifier 2009–NM–032–AD; Amendment 

39–16549; AD 2010–26–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200C, –200F, 

–400, –400D, and –400F Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Model 747– 

200C, –200F, –400, –400D, and –400F 

series airplanes. That AD currently 

requires repetitive inspections for cracks 

in the overlapping (upper) skin of the 

upper fastener row of the lap joints of 

the fuselage skin in sections 41, 42, and 

46; and related investigative and 

corrective actions, if necessary. This 

new AD expands the inspection area in 

the existing AD, and adds a 

modification of certain lap joints and 

certain post-repair inspections of the lap 

joints. Accomplishing the modification 

would end the repetitive inspections 

required by the existing AD for the 

length of lap joint that is modified. This 

AD results from a structural review of 

affected skin lap joints for widespread 

fatigue damage. We are issuing this AD 

to prevent fatigue cracking in certain lap 

joints, which could result in rapid 

depressurization of the airplane. 

DATES: This AD becomes effective 

February 1, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 1, 2011. 

On April 13, 2006 (71 FR 12122, 

March 9, 2006), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

other publication listed in the AD. 

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; e-mail 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (telephone 800–647–5527) 

is the 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: 

Nicholas Han, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6449; fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–05–09, 

Amendment 39–14506 (71 FR 12122, 

March 9, 2006). The existing AD applies 

to certain Model 747–200C, –200F, 

–400, –400D, and –400F series 

airplanes. That NPRM was published in 

the Federal Register on March 18, 2010 

(75 FR 13046). That NPRM proposed to 

continue to require repetitive 

inspections for cracks in the 

overlapping (upper) skin of the upper 

fastener row of the lap joints of the 

fuselage skin in Sections 41, 42, and 46; 

and related investigative and corrective 

actions, if necessary. That NPRM also 

proposed to expand the inspection area 

in the existing AD, and add a 

modification of certain lap joints and 

certain post-repair inspections of the lap 

joints. Accomplishing the modification 

would end the repetitive inspections 

required by the existing AD. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM. 

Request To Revise Certain Language in 

Paragraph (k) of the NPRM 

Boeing asked that we revise the 

language in paragraph (k) of the NPRM 

to indicate that additional actions are 

required in the area of the modification 

for operation beyond 15,000 total flight 

cycles after doing the proposed 

modification. Boeing stated that 

Revision 2 of Boeing Alert Service 

Bulletin 747–53A2499 is currently in 

work at the Boeing Company, and that 

Revision 2 recommends accomplishing 

additional actions after doing the 

modification. 

Since this comment was submitted, 

we have received and reviewed Boeing 

Service Bulletin 747–53A2499, Revision 

2, dated August 12, 2010. Boeing Alert 

Service Bulletin 747–53A2499, dated 

August 11, 2005; and Revision 1, dated 

October 30, 2008; were referred to in the 

NPRM as the appropriate source of 

service information for accomplishing 

the actions. No more work is necessary 

for airplanes on which Boeing Alert 

Service Bulletin 747–53A2499, Revision 

1, dated October 30, 2008, was used for 

doing the required actions. Revision 2 of 

this service bulletin moves certain 

airplanes from Group 1 to Groups 15 

and 16, adds post-modification actions, 

and contains editorial changes. 

We have revised paragraphs (c), (g), 

(h), (i), (j), and (k) of this AD to refer to 


srobinson on DSKHWCL6B1PROD with RULES