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

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


## 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—C OCKPIT 

### D OOR 

### I NSTALLATIONS 

### A FFECTED BY 

### T HIS 

### 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.


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

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—B OMBARDIER 

### S ERVICE 

### B ULLETINS FOR 

### M ODIFICATION 

### R EQUIRED BY 

### P ARAGRAPH 

### ( G 

### ) OF 

### T HIS 

### 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—B OMBARDIER 

### S ERVICE 

### B ULLETINS FOR 

### R EQUIREMENTS OF 

### P ARAGRAPH 

### ( H 

### ) OF 

### T HIS 

### 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;


## 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–