Federal Register / Vol. 74, No. 14 / Friday, January 23, 2009 / Rules and Regulations 4119 

determine if the support brackets of the 

A/C outlet extrusions between body station 

(BS) 360 and BS 907 have two-rivet 

attachment fittings in accordance with Part 2 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–25–1544, Revision 1, dated January 16, 

2008 (‘‘the service bulletin’’), except at the 

locations identified in the notes of Step 3.B.1 

of Part 1 of the Accomplishment Instructions 

of the service bulletin. 

(1) For any support bracket attached with 

three or more rivets: No further action is 

required by paragraph (f) of this AD. 

(2) For any subject support bracket having 

a two-rivet attachment fitting: Before the 

accumulation of 36,000 total flight cycles, or 

within 72 months after the effective date of 

this AD, whichever occurs later, except as 

required by paragraph (h) of this AD, do 

medium- and high-frequency eddy current 

inspections for cracking of the frame around 

the attachment holes of the support bracket, 

in accordance with Part 2 of the 

Accomplishment Instructions of the service 

bulletin. If any cracking is discovered, before 

further flight, repair the cracking in 

accordance with Part 3 of the 

Accomplishment Instructions of the service 

bulletin. 

Modification 

(g) Except as required by paragraph (h) of 

this AD: Before the accumulation of 36,000 

total flight cycles, or within 72 months after 

the effective date of this AD, whichever 

occurs later, replace the support fittings of all 

A/C outlet extrusions between BS 360 and BS 

907 with new, improved support fittings, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–25– 

1544, Revision 1, dated January 16, 2008. 

Compliance Time for Certain Airplanes 

(h) For airplanes on which Boeing Business 

Jet (BBJ) lower cabin altitude modification is 

incorporated in accordance with 

Supplemental Type Certificate ST01697SE: 

Before the accumulation of 18,000 total flight 

cycles, or within 72 months after the effective 

date of this AD, whichever occurs later, do 

the actions specified in paragraphs (f) and (g) 

of this AD. 

Actions Accomplished According to 

Previous Issue of Service Bulletin 

(i) Actions accomplished before the 

effective date of this AD according to Boeing 

Special Attention Service Bulletin 737–25– 

1544, dated October 4, 2006, are considered 

acceptable for compliance with the 

corresponding actions specified in this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, ATTN: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6447; fax (425) 917–6590; has the 

authority to approve AMOCs for this AD, if 

requested in accordance with the procedures 

found in 14 CFR 39.19. 

(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 appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD, if it is approved by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization who has been 

authorized by the Manager, Seattle ACO, to 

make those findings. For a repair method to 

be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Material Incorporated by Reference 

(k) You must use Boeing Special Attention 

Service Bulletin 737–25–1544, Revision 1, 

dated January 16, 2008, to perform the 

actions that are required by this AD, unless 

the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this document in accordance with 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) 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, for a copy of this 

service information. 

(3) You may review copies of the service 

information that is incorporated by reference 

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 or 425–227–1152. 

(4) You may also review copies of the 

service information 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 

December 18, 2008. 

Stephen P. Boyd, 

Assistant Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E8–31395 Filed 1–22–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0010; Directorate 

Identifier 2009–CE–001–AD; Amendment 

39–15792; AD 2009–02–02] 

RIN 2120–AA64 

Airworthiness Directives; Polskie 

Zaklady Lotnicze Spolka zo.o Model 

PZL M26 01 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by the aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

A detailed inspection in a M26 airplane 

revealed a significant chafing of the aileron 

control cable against the wing rib in the 

fuselage-to-wing area of transition and an 

abnormal wearing of pulleys’ gorges as well. 

Such damage can only be evidenced on 

control cables which travel in pulleys either 

limited in rotation or seized. 

If left uncorrected, this condition, which 

could also occur on the elevator or rudder 

control system, could lead to loss of one or 

more primary flight controls and consequent 

reduced controllability of the airplane. 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

February 12, 2009. 

On February 12, 2009, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive comments on this 

AD by February 23, 2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 


rwilkins on PROD1PC63 with RULES
4120 Federal Register / Vol. 74, No. 14 / Friday, January 23, 2009 / Rules and Regulations 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

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 street address for 

the Docket Office (telephone (800) 647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No. 

2008–0220, dated December 19, 2008 

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

correct an unsafe condition for the 

specified products. The MCAI states: 

A detailed inspection in a M26 airplane 

revealed a significant chafing of the aileron 

control cable against the wing rib in the 

fuselage-to-wing area of transition and an 

abnormal wearing of pulleys’ gorges as well. 

Such damage can only be evidenced on 

control cables which travel in pulleys either 

limited in rotation or seized. 

If left uncorrected, this condition, which 

could also occur on the elevator or rudder 

control system, could lead to loss of one or 

more primary flight controls and consequent 

reduced controllability of the airplane. 

For the reason stated above, this 

Airworthiness Directive requires a detailed 

inspection of flight controls and the 

correction of any discrepancy that could be 

found as a result of the inspection. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Polskie Zaklady Lotnicze Spolka zo.o. 

has issued Service Bulletin No. E/ 

62.020/2008, dated October 30, 2008. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of the 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 this State of 

Design Authority, they have notified us 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all 

information provided by the State of 

Design Authority and determined the 

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 have also required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are described in a 

separate paragraph of the AD. These 

requirements take precedence over 

those copied from the MCAI. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because chafing of the aileron 

control cable against the wing rib in the 

fuselage-to-wing area of the transition 

and an abnormal wearing of pulley 

gorges, if left uncorrected, could lead to 

loss of one or more primary controls, 

which could reduce airplane 

controllability. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2009–0010; 

Directorate Identifier 2009–CE–001– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

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 that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 


rwilkins on PROD1PC63 with RULES
Federal Register / Vol. 74, No. 14 / Friday, January 23, 2009 / Rules and Regulations 4121 

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 AD: 

2009–02–02 Polskie Zaklady Lotnicze 

Spolka zo.o: Amendment 39–15792; 

Docket No. FAA–2009–0010; Directorate 

Identifier 2009–CE–001–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 12, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Models PZL M26 01 

airplanes, serial numbers 1APP01–01 and 

1AP002–01 through 1AP002–06, certificated 

in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

‘‘A detailed inspection in a M26 airplane 

revealed a significant chafing of the aileron 

control cable against the wing rib in the 

fuselage-to-wing area of transition and an 

abnormal wearing of pulleys’ gorges as well.’’ 

‘‘Such damage can only be evidenced on 

control cables which travel in pulleys either 

limited in rotation or seized.’’ 

‘‘If left uncorrected, this condition, which 

could also occur on the elevator or rudder 

control system, could lead to loss of one or 

more primary flight controls and consequent 

reduced controllability of the airplane.’’ 

‘‘For the reason stated above, this 

Airworthiness Directive requires a detailed 

inspection of flight controls and the 

correction of any discrepancy that could be 

found as a result of the inspection.’’ 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) Before further flight, after the effective 

date of this AD, inspect the airplane’s flight 

control systems as instructed in paragraph 

III.A. of Polskie Zaklady Lotnicze Spolka 

zo.o. (PZL) Service Bulletin No. E/62.020/ 

2008, dated October 30, 2008. 

(2) If in the inspection required in 

paragraph (f)(1) of this AD any damage is 

found on the pulleys and cables of the 

aileron control system, before further flight, 

repair the damage as instructed in paragraph 

III.B. of PZL Service Bulletin No. E/62.020/ 

2008, dated October 30, 2008. 

(3) If in the inspection required in 

paragraph (f)(1) of this AD any damage is 

found on the flight control systems other 

than the pulleys and cables of the aileron 

control system, before further flight, repair 

the damage with an FAA-approved repair 

solution (see paragraph (g)(2) of this AD). 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards 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: Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4059; fax: (816) 329– 

4090. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 

Office (FSDO), or lacking a PI, your local 

FSDO. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to European Aviation Safety 

Agency (EASA) AD No. 2008–0220, dated 

December 19, 2008, and Polskie Zaklady 

Lotnicze Spolka zo.o. (PZL) Service Bulletin 

No. E/62.020/2008, dated October 30, 2008, 

for related information. 

Material Incorporated by Reference 

(i) You must use Polskie Zaklady Lotnicze 

Spolka zo.o. (PZL) Service Bulletin No. E/ 

62.020/2008, dated October 30, 2008, 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 Polskie Zaklady Lotnicze Sp. 

z.o.o., ul. Wojska Polskiego 3, 39–300 Mielec, 

Poland; telephone: +48 17 788 7574; fax: +48 

17 788 6365; e-mail: pzl@pzlmielec.com.pl; 

Internet: http://www.pzlmielec.pl/biuletyn/ 

E62–020–2008_e.pdf. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri on January 

8, 2009. 

John R. Colomy, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–776 Filed 1–22–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0935; Directorate 

Identifier 2008–NE–28–AD; Amendment 39– 

15790; AD 2009–01–11] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arriel 2B and 2B1 Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Several cases of loss of internal 

components from the Hydro Mechanical Unit 

(HMU) low fuel pressure switch HydraElectric part number (P/N) 9 550 17 956 0 

into the fuel system, have been reported on 

Arriel 2 engines. 

The loss of internal components from the 

low fuel pressure switch into the fuel system 

may lead to a rupture of the HP–LP pumps 

drive shaft shear pin, and thus to a possible 

uncommanded in-flight shutdown (IFSD). On 

a single-engine helicopter, an uncommanded 

IFSD results in an emergency autorotation 

landing and in certain conditions may lead 

to an accident. 

We are issuing this AD to prevent 

forced autorotation landing, or an 

accident. 


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