Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations 63169 

attention of the person identified in the 

Related Information section of this AD. 

(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. 

(k) Related Information 

For more information about this AD, 

contact Hal Horsburgh, Aerospace Engineer, 

FAA, Atlanta ACO, 1701 Columbia Avenue, 

College Park, Georgia 30337; telephone: (404) 

474–5553; fax: (404) 474–5606; e-mail: 

hal.horsburgh@faa.gov. 

(l) Material Incorporated by Reference 

(1) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. The 

Director of the Federal Register approved the 

incorporation by reference (IBR) under 5 

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

following service information on November 

16, 2011: 

(i) Premier Aircraft Service Work 

Instruction PAS–WI–MSB–40–2011–001, 

dated March 4, 2011; and 

(ii) Premier Aircraft Service Mandatory 

Service Bulletin No. PAS–MSB–40–2011– 

001, dated March 4, 2011. 

(2) If you accomplish the optional actions 

specified by this AD, you must use the 

following service information to perform 

those actions. The Director of the Federal 

Register approved the incorporation by 

reference (IBR) of the following service 

information on November 16, 2011: 

(i) Premier Aircraft Service Service 

Bulletin No. PAS–SB–40–2011–002, dated 

August 18, 2011; 

(ii) Seamech International Inc. Vapor Cycle 

Air Conditioning with Automatic Climate 

Control Instructions for Continued 

Airworthiness, ASI–772216A, Revision G, 

dated August 9, 2011; 

(iii) Seamech International Inc. Kit 

Compressor Mounting, Drawing SII 2216155, 

Revision D, dated July 21, 2011; 

(iv) DER Services Installation Instructions 

Engineering Order EO–2006–020–1, Revision 

F, dated August 18, 2011. 

(3) For service information identified in 

this AD, contact Premier Aircraft Service, 

5540 NW 23 Avenue Hangar 14, Ft. 

Lauderdale, FL 33309, telephone: (954) 771– 

0411; fax: (954) 334–1489; Internet: http:// 

www.flypas.com. 

(4) You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

(5) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at 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 Kansas City, Missouri, on 

October 3, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–26001 Filed 10–11–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0479; Directorate 

Identifier 2010–NM–154–AD; Amendment 

39–16827; AD 2011–21–04] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier 

Inc. Model DHC–8–102, –103, –106, 

–201, –202, –301, –311, and –315 

Airplanes; Equipped With Certain 

Cockpit Door Installations 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

This 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: 

During structural testing of the cockpit 

door, it was observed that the door lower 

hinge block rotated which resulted in 

disengagement of the mating hinge pin and 

excessive door deflection. The lower hinge 

block rotated because it was attached to its 

support structure with only one attachment 

bolt, which prevented it from reacting to any 

moment force. This condition, if not 

corrected, could result in breakage and 

uncontrolled release of the cockpit door 

under certain decompression situations. 

After incorporation of Modsum 8Q900267 

* * *, an operator reported a failure to 

complete the cockpit door removal function 

test. This condition, if not corrected, could 

result in the inability to remove the cockpit 

door for emergency egress. * * * 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

November 16, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 16, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of Bombardier Service Bulletin 8–52–54, 

Revision A, dated November 5, 2004, as 

of July, 18, 2006 (71 FR 34006, June 13, 

2006). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Andreas Rambalakos, Aerospace 

Engineer, Airframe and Mechanical 

Systems Branch, ANE–171, FAA, New 

York Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7345; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on June 8, 2011 (76 FR 33173), 

and proposed to supersede AD 2006– 

12–16, Amendment 39–14642 (71 FR 

34006, June 13, 2006). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During structural testing of the cockpit 

door, it was observed that the door lower 

hinge block rotated which resulted in 

disengagement of the mating hinge pin and 

excessive door deflection. The lower hinge 

block rotated because it was attached to its 

support structure with only one attachment 

bolt, which prevented it from reacting to any 

moment force. This condition, if not 

corrected, could result in breakage and 

uncontrolled release of the cockpit door 

under certain decompression situations. 

After incorporation of Modsum 8Q900267 

* * *, an operator reported a failure to 

complete the cockpit door removal function 

test. This condition, if not corrected, could 

result in the inability to remove the cockpit 

door for emergency egress. Therefore, * * * 

this [Canadian] directive is issued to require 

rework of the cockpit door striker plate and 

replacement of the latch block for the 

affected aircraft serial numbers. * * * 

You may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. The 

commenter supports the NPRM (76 FR 

33173, June 8, 2011). 

Conclusion 

We reviewed the available data, 

including the comment received, and 

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63170 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 17 products of U.S. registry. 

The actions that are required by AD 

2006–12–16 (71 FR 34006, June 13, 

2006) and retained in this AD take 

between 3 and 6 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $2,000 per product. Based on 

these figures, the estimated cost of the 

currently required actions is between 

$2,255 and $2,510 per product. 

We estimate that it will take about 3 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$2,000 per product. 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 

this AD to the U.S. operators to be 

$38,335, or $2,255 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 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 this AD: 

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 AD and placed it in the AD docket. 

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 the NPRM (76 FR 33173, June 

8, 2011), 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. 

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 

removing Amendment 39–14642 (71 FR 

34006, June 13, 2006) and adding the 

following new AD: 

2011–21–04 Bombardier Inc.: Amendment 

39–16827. Docket No. FAA–2011–0479; 

Directorate Identifier 2010–NM–154–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 16, 2011. 

Affected ADs 

(b) This AD supersedes AD 2006–12–16, 

Amendment 39–14642 (71 FR 34006, June 

13, 2006). 

Applicability 

(c) This AD applies to Bombardier Model 

DHC–8–102, –103, –106, –201, –202, –301, 

–311, and –315 airplanes, certificated in any 

category; serial numbers (S/Ns) 003 through 

557 inclusive; equipped with cockpit door 

installation part numbers (P/Ns) identified in 

table 1 of this AD. 

TABLE 1—COCKPIT DOOR

INSTALLATIONS AFFECTED BY THIS AD 

P/N Dash number(s) 

82510074 ........................... All. 

82510294 ........................... All. 

82510310 ........................... –001. 

8Z4597 ............................... –001. 

H85250010 ........................ All. 

82510700 ........................... All. 

82510704 ........................... All except ¥502 

and ¥503. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 52: Doors. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During structural testing of the cockpit 

door, it was observed that the door lower 

hinge block rotated which resulted in 

disengagement of the mating hinge pin and 

excessive door deflection. The lower hinge 

block rotated because it was attached to its 

support structure with only one attachment 

bolt, which prevented it from reacting to any 

moment force. This condition, if not 

corrected, could result in breakage and 

uncontrolled release of the cockpit door 

under certain decompression situations. 

After incorporation of Modsum 8Q900267 

* * * an operator reported a failure to 

complete the cockpit door removal function 

test. This condition, if not corrected, could 

result in the inability to remove the cockpit 

door for emergency egress. * * * 

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. 

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Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations 63171 

Restatement of Requirements of AD 2006– 

12–16 Amendment 39–14642 (71 FR 34006, 

June 13, 2006), With New Service 

Information 

Modification 

(g) Within 24 months after July 18, 2006 

(the effective date of AD 2006–12–16 

Amendment 39–14642 (71 FR 34006, June 

13, 2006)), modify the cockpit door from a 

single-point attachment to a two-point 

attachment in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin in table 2 of this 

AD. For airplane serial numbers 452, 464, 

490, 506, and 508 through 557 inclusive: 

After the effective date of this AD, use 

Bombardier Service Bulletin 8–52–58, 

Revision A, dated November 17, 2006. 

TABLE 2—BOMBARDIER SERVICE BULLETINS FOR MODIFICATION REQUIRED BY PARAGRAPH (G) OF THIS AD 

Use this Bombardier Service Bulletin— For airplane serial numbers— 

8–52–54, Revision A, dated November 5, 2004 ...................................... 003 through 451 inclusive, 453 through 463 inclusive, 465 through 489 

inclusive, 491 through 505 inclusive, and 507. 

8–52–58, dated May 12, 2004, or Revision A, dated November 17, 

2006.

452, 464, 490, 506, and 508 through 557 inclusive. 

Note 1: Bombardier Service Bulletin 8–52– 

54, Revision A, dated November 5, 2004, 

refers to Bombardier Series 100/300 

Modification Summary (Modsum) 8Q100859 

as an additional source of guidance for 

installing a hinge pin with a two-point 

attachment. Bombardier Service Bulletin 8– 

52–58, dated May 12, 2004, or Revision A, 

dated November 17, 2006, refers to 

Bombardier Series 100/300 Modsum 

8Q900267 as an additional source of 

guidance for reworking and installing the 

cockpit door, and reworking the lower hinge 

attachment to provide a downward-facing 

pin with a two-point attachment. 

Prior/Concurrent Requirements 

(h) Prior to or concurrently with the 

modification in paragraph (g) of this AD, do 

the applicable actions specified in table 3 of 

this AD, in accordance with a method 

approved by either the Manager, New York 

Aircraft Certification (ACO), FAA; or 

Transport Canada Civil Aviation (TCCA) (or 

its delegated agent). 

TABLE 3—BOMBARDIER SERVICE BULLETINS FOR REQUIREMENTS OF PARAGRAPH (H) OF THIS AD 

For airplanes affected by Bombardier Service 

Bulletin— That have these serial numbers— Do these actions— 

8–52–54, Revision A, dated November 5, 2004 003 through 407 inclusive, 409 through 412 

inclusive, and 414 through 433 inclusive.

Rework the cockpit door emergency release. 

Install a new label regarding alternate release 

of the door. 

8–52–58, dated May 12, 2004, or Revision A, 

dated November 17, 2006.

452, 464, 490, 506, and 508 through 557 inclusive.Install the cockpit door. 

Note 2: Bombardier Service Bulletin 8–52– 

54, Revision A, dated November 5, 2004, 

refers to De Havilland Aircraft of Canada, 

Limited, Modification 8/2337 as an 

additional source of guidance for reworking 

the cockpit door emergency release; and 

Modification 8/3339 as additional source of 

guidance for installing a new label regarding 

alternate release of the door; on airplanes 

having serial numbers 003 through 407 

inclusive, 409 through 412 inclusive, and 414 

through 433 inclusive. 

Note 3: Bombardier Service Bulletins 8– 

52–58, dated May 12, 2004; and Revision A, 

dated November 17, 2006; refer to 

Bombardier Modsum 8Q200015, as an 

additional source of guidance for installing 

the cockpit door, on airplanes having serial 

numbers 452, 464, 490, 506, and 508 through 

557 inclusive. 

Actions Done in Accordance With Previous 

Revision of Service Bulletin 

(i) Actions done before July 18, 2006, in 

accordance with Bombardier Service Bulletin 

8–52–54, dated May 12, 2004, are acceptable 

for compliance with the corresponding 

requirements in paragraph (g) of this AD. 

New Requirements of This AD 

(j) For airplanes having S/N 452, 464, 490, 

506, and 508 through 557 inclusive, and on 

which the requirements in paragraph (g) of 

this AD have been done as of the effective 

date of this AD: Within 12 months after the 

effective date of this AD rework the cockpit 

door striker plate and replace the latch block, 

in accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–52–61, dated October 20, 2006. 

(k) For airplanes having S/Ns 452, 464, 

490, 506, and 508 through 557 inclusive, and 

on which the requirements in paragraph (g) 

of this AD have not been done as of the 

effective date of this AD: Prior to or 

concurrently with doing the modification 

required in paragraph (g) of this AD, rework 

the cockpit door striker plate and replace the 

latch block, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–52–61, dated October 20, 

2006. 

FAA AD Differences 

Note 4: 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, New York Aircraft 

Certification Office, ANE–170, 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 ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, New York 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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. 

Related Information 

(m) Refer to MCAI Canadian Airworthiness 

Directive CF–2005–34R1, dated August 15, 

2007; Bombardier Service Bulletin 8–52–54, 

Revision A, dated November 5, 2004; 

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63172 Federal Register / Vol. 76, No. 197 / Wednesday, October 12, 2011 / Rules and Regulations 

Bombardier Service Bulletin 8–52–58, 

Revision A, dated November 17, 2006; and 

Bombardier Service Bulletin 8–52–61, dated 

October 20, 2006; for related information. 

Material Incorporated by Reference 

(n) You must use the following service 

information to do the applicable actions 

required by this AD, unless the AD specifies 

otherwise. The Director of the Federal 

Register approved the incorporation by 

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

CFR Part 51 of the following service 

information on the date specified: 

(1) Bombardier Service Bulletin 8–52–58, 

Revision A, dated November 17, 2006, 

approved for IBR November 16, 2011; 

(2) Bombardier Service Bulletin 8–52–61, 

dated October 20, 2006, approved for IBR 

November 16, 2011; 

(3) Bombardier Service Bulletin 8–52–54, 

Revision A, dated November 5, 2004, 

approved for IBR July 18, 2006 (71 FR 34006, 

June 13, 2006). 

(4) For service information identified in 

this AD, contact Bombardier Inc., Q–Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

e-mail thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(5) 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. 

(6) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on 

September 23, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–25770 Filed 10–11–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0033; Directorate 

Identifier 2009–NM–099–AD; Amendment 

39–16737; AD 2011–14–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 767 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) 

that applies to all Model 767 airplanes. 

The existing AD currently requires 

repetitive detailed and high frequency 

eddy current (HFEC) inspections of the 

station (STA) 1809.5 bulkhead for 

cracking, and corrective actions if 

necessary. This AD expands the 

inspection area to include the vertical 

inner chord at STA 1809.5. This AD 

results from reported fatigue cracking in 

the vertical inner chord and the forward 

outer chord while doing the detailed 

inspection of the horizontal inner chord 

at STA 1809.5. We are issuing this AD 

to detect and correct fatigue cracking in 

the bulkhead structure at STA 1809.5 

and the vertical inner chord at STA 

1809.5, which could result in failure of 

the bulkhead structure for carrying the 

flight loads of the horizontal stabilizer, 

and consequent loss of controllability of 

the airplane. 

DATES: This AD becomes effective 

November 16, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 16, 2011. 

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; phone: 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: 

Berhane Alazar, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, 

SW., Renton, Washington 98057–3356; 

phone: 425–917–6577; fax: 425–917– 

6590; e-mail: Berhane.Alazar@faa.gov. 

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 2006–24–04, 

Amendment 39–14833 (71 FR 68432, 

November 27, 2006). The existing AD 

applies to all Model 767 airplanes. That 

NPRM was published in the Federal 

Register on February 8, 2010 (75 FR 

6154). That NPRM proposed to continue 

to require repetitive detailed and HFEC 

inspections of the STA 1809.5 bulkhead 

for cracking, and corrective actions if 

necessary. That NPRM also proposed to 

expand the inspection area to include 

the vertical inner chord at STA 1809.5. 

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 (75 FR 

6154, February 8, 2010). 

Support for the NPRM 

Continental Airlines (CAL) stated that 

it supports the intent of the NPRM (75 

FR 6154, February 8, 2010). 

Request To Revise Paragraph (k)(1) of 

the NPRM 

Boeing requested that we revise the 

compliance time in paragraph (k)(1) of 

the NPRM (75 FR 6154, February 8, 

2010) to state ‘‘whichever occurs later’’ 

rather than ‘‘whichever occurs first.’’ 

Boeing stated that a similar AD, AD 

2006–24–04 (71 FR 68432, November 

27, 2006) (the AD being superseded), 

provides a choice of the later of two 

compliance times. Boeing stated that 

changing the compliance time language 

in paragraph (k)(1) of the NPRM would 

make this AD consistent with AD 2006– 

24–04. 

We agree with the request for the 

reasons provided by the commenter, 

and we have revised paragraph (k)(1) of 

this final rule accordingly. 

Request To Add Model 767–300BCF 

and 767–200SF Structural Repair 

Manuals (SRMs) To Clarify 

Terminating Action 

Boeing requested that we specify 

Model 767–300BCF and Model 767– 

200SF SRMs in paragraphs (i) and (m) 

of the NPRM (75 FR 6154, February 8, 

2010) to clarify the terminating action 

for converted Model 767–200 and –300 

series airplanes. Boeing stated that some 

Model 767–300 airplanes have been 

converted to Model 767–300BCF 

airplanes, and some Model 767–200 

airplanes have been converted to Model 

767–200SF airplanes. Boeing stated that 

the Model 767–200SF and Model 767– 

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