This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

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REGISTER issue of each week.

Rules and Regulations Federal Register

1 

Vol. 77, No. 1 

Tuesday, January 3, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1062; Directorate 

Identifier 2011–NM–038–AD; Amendment 

39–16907; AD 2011–27–05] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all Saab AB, Saab Aerosystems Model 

340A (SAAB/SF340A) and SAAB 340B 

airplanes. That AD currently requires an 

inspection of the main landing gear 

(MLG) separation bolt harness for 

broken wires and corroded connectors, 

and corrective actions if necessary; and 

for certain airplanes, a modification of 

the MLG separation bolt’s electrical 

harness. This new AD requires 

replacement of the separation bolt 

harness. This AD was prompted by 

reports of broken wires and corroded 

connectors in the SAAB 340 MLG 

emergency release system. We are 

issuing this AD to prevent improper 

release of the MLG during an emergency 

situation, possibly resulting in damage 

to the airplane during landing and 

injury to the occupants. 

DATES: This AD becomes effective 

February 7, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 7, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of July 29, 2004 (69 FR 

35235, June 24, 2004). 

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: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1112; fax (425) 227–1149. 

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 October 11, 2011 (76 FR 

62656), and proposed to supersede AD 

2004–12–03, Amendment 39–13662 (69 

FR 35235, June 24, 2004). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

In 2003, a number of reports had been 

received concerning broken wires and 

corroded connectors in the SAAB 340 main 

landing gear (MLG) emergency release 

system. The investigation results showed that 

these were due to improper repairs and 

installations, not conforming to the approved 

type design. 

This condition, if not corrected, could 

inhibit the functioning of the separation bolt, 

preventing proper release of the MLG during 

an emergency situation, possibly resulting in 

damage to aeroplane during landing and 

injury to the occupants. 

To address that unsafe condition, Swedish 

AD (SAD) 1–186 was issued to require an 

inspection and, depending on findings, 

corrective action, in accordance with SAAB 

Service Bulletin (SB) 340–32–127. 

Subsequently, Saab introduced a 

modification to ensure correct functioning of 

the MLG emergency release system. 

Accomplishment of that modification (SAAB 

SB 340–32–128) was made mandatory by 

SAD 1–189 [which corresponds to FAA AD 

2004–12–03 Amendment 39–13662 (69 FR 

35235, June 24, 2004)]. 

Since that [SAD] AD was issued, service 

experience has shown that this modification 

does not fully meet the expected results. 

Prompted by these findings, SAAB has 

developed an improved separation bolt 

harness with a new routing. 

For the reasons described above, this 

[EASA] AD requires replacement of the 

current separation bolt harness Part Number 

(P/N) 7292520–678 with the improved unit, 

P/N 7292520–691. 

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 

received no comments on the NPRM (76 

FR 62656, October 11, 2011) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

62656, October 11, 2011) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 62656, 

October 11, 2011). 

Differences Between This AD and the 

Mandatory Continuing Airworthiness 

Information (MCAI) or Service 

Information 

This AD differs from the MCAI and/ 

or service information as follows: 

Although the MCAI states not to install 

a separation bolt having P/N 7292520– 

678 on any airplane after modification 

of the airplane, this AD states not to 

install a separation bolt having P/N 

7292520–678 on any airplane as of the 

effective date of this AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 111 products of U.S. registry. 

The actions that are required by AD 

2004–12–03, Amendment 39–13662 (69 

FR 35235, June 24, 2004), and retained 

in this AD take about 6 work-hours per 

product, at an average labor rate of $85 

per work-hour. Required parts cost 

about $1,475 per product. Based on 

these figures, the estimated cost of the 

currently required actions is 1,985 per 

product. 

We estimate that it will take about 10 

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 

$1,790 per product. Where the service 

information lists required parts costs 


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2 Federal Register / Vol. 77, No. 1 / Tuesday, January 3, 2012 / Rules and Regulations 

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 

$96,140, or $2,640 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 62656, 

October 11, 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 39–13662 (69 FR 

35235, June 24, 2004) and adding the 

following new AD: 

2011–27–05 Saab AB, Saab Aerosystems: 

Amendment 39–16907. Docket No. 

FAA–2011–1062; Directorate Identifier 

2011–NM–038–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective February 7, 2012. 

(b) Affected ADs 

This AD supersedes AD 2004–12–03, 

Amendment 39–13662 (69 FR 35235, June 

24, 2004). 

(c) Applicability 

This AD applies to Saab AB, Saab 

Aerosystems Model 340A (SAAB/SF340A) 

and SAAB 340B airplanes, all serial numbers, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32: Landing gear. 

(e) Reason 

This AD was prompted by reports of 

broken wires and corroded connectors in the 

SAAB 340 MLG emergency release system. 

We are issuing this AD to prevent improper 

release of the MLG during an emergency 

situation, possibly resulting in damage to the 

airplane during landing and injury to the 

occupants. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2004– 

12–03, Amendment 39–13662 (69 FR 35235, 

JUNE 24, 2004), With Changes 

(g) Inspection 

Within 3 months after July 29, 2004 (the 

effective date of AD 2004–12–03, 

Amendment 39–13662 (69 FR 35235, June 

24, 2004)), perform an inspection of the 

MLG’s separation bolt harness for broken 

wires and corroded connectors, and any 

applicable corrective actions by doing all of 

the actions, in accordance with the 

Accomplishment Instructions of Saab Service 

Bulletin 340–32–127, dated December 18, 

2002; or Revision 01, dated January 23, 2003. 

Perform the inspection/corrective actions in 

accordance with Saab Service Bulletin 340– 

32–127, dated December 18, 2002; or 

Revision 01, dated January 23, 2003. Perform 

any applicable corrective actions before 

further flight. 

(h) Concurrent Service Bulletins 

For Model SAAB SF340A series airplanes: 

Within 12 months after July 29, 2004, do the 

actions specified in table 1 of this AD, as 

applicable. 

TABLE 1—PRIOR/CONCURRENT ACTIONS

For airplanes with serial 

numbers— Accomplish all actions associated with— According to the accomplishment instructions of— 

004 through 108 inclusive .... Modifying the MLG separation bolt’s electrical harness Saab Service Bulletin 340-32-041, Revision 01, dated 

October 9, 1987. 

004 through 078 inclusive .... Modifying the MLG separation bolt’s electrical harness Saab Service Bulletin 340-32-028, Revision 01, dated 

November 25, 1986. 

(i) New Requirements of This AD 

Within 12 months after the effective date 

of this AD: Replace the separation bolt 

harnesses having part number (P/N) 

7292520–678 with separation bolt harnesses 

having P/N 7292520–691, in accordance with 

the Accomplishment Instructions of Saab 

Service Bulletin 340–32–139, Revision 01, 

dated November 1, 2010. 


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Federal Register / Vol. 77, No. 1 / Tuesday, January 3, 2012 / Rules and Regulations 3 

(j) Parts Installation 

As of the effective date of this AD, no 

person may install a separation bolt harness 

having P/N 7292520–678, on any airplane. 

(k) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Actions done before the effective date of 

this AD in accordance with Saab Service 

Bulletin 340–32–139, dated January 12, 2010, 

are acceptable for compliance with the 

requirements of paragraph (i) of this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1112; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

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. 

(m) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0003, dated January 17, 2011, 

and the service information specified in 

paragraphs (m)(1) through (m)(5) of this AD, 

as applicable, for related information. 

(1) Saab Service Bulletin 340–32–139, 

Revision 01, dated November 1, 2010. 

(2) Saab Service Bulletin 340–32–127, 

dated December 18, 2002. 

(3) Saab Service Bulletin 340–32–127, 

Revision 01, dated January 23, 2003. 

(4) Saab Service Bulletin 340–32–041, 

Revision 01, dated October 9, 1987. 

(5) Saab Service Bulletin 340–32–028, 

Revision 01, dated November 25, 1986. 

(n) 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) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51 on the date 

specified: 

(i) Saab Service Bulletin 340–32–028, 

Revision 01, dated November 25, 1986, 

approved for IBR July 29, 2004 (69 FR 35235, 

June 24, 2004). 

(ii) Saab Service Bulletin 340–32–041, 

Revision 01, dated October 9, 1987, approved 

for IBR July 29, 2004 (69 FR 35235, June 24, 

2004). 

(iii) Saab Service Bulletin 340–32–127, 

dated December 18, 2002, approved for IBR 

July 29, 2004 (69 FR 35235, June 24, 2004). 

(iv) Saab Service Bulletin 340–32–127, 

Revision 01, dated January 23, 2003, 

approved for IBR July 29, 2004 (69 FR 35235, 

June 24, 2004). 

(v) Saab Service Bulletin 340–32–139, 

Revision 01, dated November 1, 2010, 

approved for IBR February 7, 2012. 

(2) For service information identified in 

this AD, contact Saab AB, Saab Aerosystems, 

SE–581 88, Linko ̈ping, Sweden; telephone 

+46 13 18 5591; fax +46 13 18 4874; email 

saab2000.techsupport@saabgroup.com; 

Internet http://www.saabgroup.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 23, 2011. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–33565 Filed 12–30–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1061; Directorate 

Identifier 2011–NM–053–AD; Amendment 

39–16908; AD 2011–27–06] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model FALCON 7X 

airplanes equipped with certain ram air 

turbine (RAT) transformer rectifier units 

(TRUs). This AD was prompted by a 

report of incorrect design of the TRU 

part of the RAT system. This AD 

requires replacing any affected RAT 

TRU with a modified RAT TRU. We are 

issuing this AD to prevent loose internal 

wiring in the RAT generator, which 

could result in degraded direct current 

power to essential airplane systems 

while the RAT is deployed, which could 

adversely affect continued safe flight 

and landing of the airplane. 

DATES: This AD becomes effective 

February 7, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of February 7, 2012. 

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: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

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 October 11, 2011 (76 FR 

62671). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

The manufacturer of the Transformer 

Rectifier Unit (TRU) part of the Ram Air 

Turbine (RAT) system has identified an 

incorrect design of the part. 

The internal wiring that conducts the high 

voltage alternative current from the RAT 

generator may become loose due to 

insufficient crimping of the wire and 

contacts. 

This condition, if not corrected, and if 

occurring while the RAT is deployed, could 

result in a degraded direct current power 

which is distributed to essential aeroplane 

systems and therefore aeroplane operations 

might be impaired. 

To address this unsafe condition, the 

manufacturer of the RAT TRU has developed 

an improved RAT TRU with a new Part 

Number (P/N). 

This [European Aviation Safety Agency 

(EASA)] AD requires replacement of the 

affected RAT TRU by a modified RAT TRU. 

You may obtain further information by 

examining the MCAI in the AD docket. 


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