12176 Federal Register / Vol. 77, No. 40 / Wednesday, February 29, 2012 / Rules and Regulations 

November 2, 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 adding 

the following new AD: 

2012–02–18 DASSAULT AVIATION: 

Amendment 39–16941. Docket No. 

FAA–2011–1166; Directorate Identifier 

2010–NM–169–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 4, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to DASSAULT AVIATION 

Model MYSTERE-FALCON 50 airplanes, all 

serial numbers, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57: Wings. 

(e) Reason 

This AD was prompted by reports of 

cracking of the flap tracks. We are issuing 

this AD to prevent cracking of the flap tracks, 

which could lead to flap asymmetry and loss 

of control of the airplane. 

(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. 

(g) Actions 

Within 30 days after the effective date of 

the AD, revise the maintenance program to 

include ‘‘Non-Destructive Check of Flap 

Tracks 2 and 5,’’ Maintenance Procedure 57– 

607, of Chapter 5–40, ‘‘Airworthiness 

Limitations,’’ of the Dassault Falcon 50/50EX 

Maintenance Manual, Revision 21, dated 

June 2011. The initial compliance time for 

doing the check is prior to the accumulation 

of 7,900 total flight cycles or within 600 

flight cycles after the effective date of this 

AD, whichever occurs later. 

(h) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (i)(1) of 

this AD. 

(i) 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: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–227–1137; 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 

(j) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2010–0080, dated April 29, 2010; and ‘‘NonDestructive Check of Flap Tracks 2 and 5,’’ 

Maintenance Procedure 57–607, of Chapter 

5–40, ‘‘Airworthiness Limitations,’’ of the 

Dassault Falcon 50/50EX Maintenance 

Manual, Revision 21, dated June 2011; for 

related information. 

(k) 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. 

(i) ‘‘Non-Destructive Check of Flap Tracks 

2 and 5,’’ Maintenance Procedure 57–607, of 

Chapter 5–40, ‘‘Airworthiness Limitations,’’ 

of the Dassault Falcon 50/50EX Maintenance 

Manual, Revision 21, dated June 2011. 

(A) Only the title page of Chapter 5–40 

specifies the revision level of 21, dated June 

2011; the remaining pages show only the 

revision date of June 2011. 

(B) The pages of the maintenance 

procedure show a revision date of January 

2009. 

(2) For service information identified in 

this AD, contact Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon.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 January 

26, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–3908 Filed 2–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1067; Directorate 

Identifier 2011–NM–034–AD; Amendment 

39–16944; AD 2012–03–03] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Fokker Services B.V. Model F.27 Mark 

050 and F.28 Mark 0070 and 0100 

airplanes. This AD was prompted by 

reports that the brightness of the tritium 

exit signs and lighting strips 

deteriorated below accepted levels. This 

AD requires a detailed inspection of 

tritium exit signs and emergency 

lighting strips, and replacement if 

necessary. We are issuing this AD to 

detect and correct insufficient 

brightness of the tritium exit signs and 

lighting strips, which could lead to an 

unsafe evacuation during an emergency, 

possibly resulting in injury to 

occupants. 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 40 / Wednesday, February 29, 2012 / Rules and Regulations 12177 

DATES: This AD becomes effective April 

4, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 4, 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 

62658). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

As required by current certification 

standards, each transport aeroplane has 

passenger compartment exit signs and 

emergency lighting strips installed to locate 

the emergency exits. A number of these strips 

and signs are not electrically powered, but 

are self illuminated by means of a hydrogen 

isotope, known as Tritium. As this isotope 

decays over time, these signs will [lose] their 

brightness. 

To remain compliant with regulations, 

Tritium exit signs and lighting strips should 

be replaced when their brightness has 

deteriorated below accepted levels. 

Currently, the Maintenance Review Board 

(MRB) Maintenance Planning Document does 

not include an inspection task for signs and 

strips containing Tritium. 

This condition, if not detected and 

corrected, could result in insufficiently bright 

exit signs and lighting strips, preventing safe 

evacuation during an emergency, possibly 

resulting in injury to occupants. 

To correct this unsafe condition, EASA 

issued AD 2010–0200, which required [a 

detailed visual] inspection of the brightness 

of all Tritium exit signs and strips and, 

depending on findings, replacement of 

insufficiently bright signs and lighting strips. 

Following the issuance of [EASA] AD 

2010–0200, Fokker Services discovered that 

one Service Bulletin (SB), SBF100–33–023, 

contained errors in the two groups of 

aeroplane serial numbers and, consequently, 

in the related instructions for those 

aeroplanes in that SB. 

For the reasons described above, this new 

[EASA] AD retains the requirements of EASA 

AD 2010–0200, which is superseded, amends 

the Applicability and refers to Revision 1 of 

SBF100–33–023 for the accomplishment 

instructions. 

Note: The MRB document will be updated 

before July 2011 to include an appropriate 

maintenance task to ensure that the Tritium 

exit signs and lighting strips meet the 

minimum brightness requirements. 

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 

62658, October 11, 2011). 

Additional Change Made to This Final 

Rule 

We have revised the heading for and 

wording in paragraph (i) of this AD; this 

change has not changed the intent of 

that paragraph. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the change described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

62658, 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 62658, 

October 11, 2011). 

Costs of Compliance 

We estimate that this AD will affect 

4 products of U.S. registry. We also 

estimate that it will take about 1 workhour per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $340, or $85 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 2 work-hours and require parts 

costing $833, for a cost of $1,003 per 

product. We have no way of 

determining the number of products 

that may need these actions. 

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 affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

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 62658, 

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, 


tkelley on DSK3SPTVN1PROD with RULES
12178 Federal Register / Vol. 77, No. 40 / Wednesday, February 29, 2012 / Rules and Regulations 

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: 

2012–03–03 Fokker Services B.V.: 

Amendment 39–16944. Docket No. 

FAA–2011–1067; Directorate Identifier 

2011–NM–034–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective April 4, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Fokker Services B.V. 

Model airplanes identified in paragraphs 

(c)(1), (c)(2), and (c)(3) of this AD, certificated 

in any category. 

(1) F.27 Mark 050 airplanes having serial 

numbers (S/Ns): 20104, 20105, 20121 

through 20123 inclusive, 20130 through 

20135 inclusive, 20141 through 20145 

inclusive, 20150, 20156 through 20176 

inclusive, 20178 through 20180 inclusive, 

20182 through 20199 inclusive, 20202, 20204 

through 20207 inclusive, 20210, 20211, 

20213 through 20252 inclusive, 20254 

through 20266 inclusive, 20270 through 

20279 inclusive, 20281, 20283 through 20288 

inclusive, 20296 through 20303 inclusive, 

20306, 20307, 20312, 20313, 20316, 20317, 

20328, 20331, 20333, and 20335. 

(2) F.28 Mark 0070 and 0100 airplanes 

having S/Ns: 11257, 11258, 11262, 11264 

through 11266 inclusive, 11287, 11301, 

11317, 11340, 11342, 11352 through 11356 

inclusive, 11360, 11368 through 11370 

inclusive, 11376, 11377, 11385, 11395, 

11402, 11403, 11405 through 11408 

inclusive, 11411 through 11419 inclusive, 

11425 through 11428 inclusive, 11434 

through 11437 inclusive, 11447 through 

11449 inclusive, 11457 through 11459 

inclusive, 11467, 11469, 11478, 11479, 

11481, 11482, 11487, 11492 through 11495 

inclusive, 11497, 11498, 11501, 11503, 

11506, 11507, 11509, 11514, 11521, 11528, 

11529, 11532, 11536 through 11541 

inclusive, 11543, 11545, 11547, 11549, 

11551, 11553 through 11583 inclusive, and 

11585. 

(3) F.28 Mark 0100 airplanes, if in a postFokker Service Bulletin SBF100–52–060 

configuration, having S/Ns: 11244 through 

11256 inclusive, 11259 through 11261 

inclusive, 11263, 11267 through 11286 

inclusive, 11288 through 11300 inclusive, 

11302 through 11316 inclusive, 11318 

through 11339 inclusive, 11341, 11343 

through 11351 inclusive, 11357 through 

11367 inclusive, 11371 through 11375 

inclusive, 11378 through 11384 inclusive, 

11386 through 11394 inclusive, 11396 

through 11401 inclusive, 11404, 11409, 

11410, 11420 through 11424 inclusive, 11429 

through 11433 inclusive, 11438 through 

11446 inclusive, 11450 through 11456 

inclusive, 11460 through 11466 inclusive, 

11468, 11470 through 11477 inclusive, 

11480, 11483 through 11486 inclusive, 11488 

through 11491 inclusive, 11496, 11499, 

11500, 11502, 11504, 11505, 11508, 11510 

through 11513 inclusive, 11515 through 

11520 inclusive, 11522, 11523, and 11527. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 33: Lights. 

(e) Reason 

This AD was prompted by reports that the 

brightness of the tritium exit signs and 

lighting strips deteriorated below accepted 

levels. We are issuing this AD to detect and 

correct insufficient brightness of the tritium 

exit signs and lighting strips, which could 

lead to an unsafe evacuation during an 

emergency, possibly resulting in injury to 

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. 

(g) Actions 

Within six months after the effective date 

of this AD, do a detailed visual inspection of 

the tritium exit signs and emergency lighting 

strips for required brightness, in accordance 

with the Accomplishment Instructions of 

Fokker Service Bulletin SBF50–33–038, 

dated July 5, 2010; or SBF100–33–023, 

Revision 1, dated November 4, 2010; as 

applicable. If any exit signs or emergency 

lighting strips are insufficiently bright, before 

further flight, replace the exit signs or 

emergency lighting strips, in accordance with 

the Accomplishment Instructions of Fokker 

Service Bulletin SBF50–33–038, dated July 5, 

2010; or SBF100–33–023, Revision 1, dated 

November 4, 2010; as applicable. A review of 

airplane maintenance records is acceptable in 

lieu of the inspection in this paragraph if the 

tritium exit signs and emergency lighting 

strips can be conclusively determined to 

have been manufactured in 2003 or earlier, 

from that review; however, the replacement 

in this paragraph must be accomplished 

before further flight after doing the review. 

(h) Parts Installation 

As of the effective date of this AD, no 

person may install any tritium exit signs or 

emergency lighting strips if the 

manufacturing date is seven years or more 

before the intended installation date, or if the 

manufacturing date cannot be determined; 

unless the tritium exit sign or emergency 

lighting strip has been inspected in 

accordance with paragraph (g) of this AD, 

and does not need replacement. 

(i) Credit for Previous Actions 

This paragraph provides credit for 

inspection and replacement of the tritium 

exit sign or emergency lighting strip, as 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Fokker Service Bulletin 

SBF100–33–023, dated July 5, 2010, as 

applicable. 

(j) 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: 

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. 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. 

(k) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2010–0261, 

dated December 9, 2010; for related 

information. 

(1) Fokker Service Bulletin SBF50–33–038, 

dated July 5, 2010; and 

(2) Fokker Service Bulletin SBF100–33– 

023, Revision 1, dated November 4, 2010. 

(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) of the 

following service information under 5 U.S.C. 

552(a) and 1 CFR part 51: 

(i) Fokker Service Bulletin SBF50–33–038, 

dated July 5, 2010. 

(ii) Fokker Service Bulletin SBF100–33– 

023, Revision 1, dated November 4, 2010. 

(2) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; email technicalservices.

fokkerservices@stork.com; Internet http://

www.myfokkerfleet.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 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 40 / Wednesday, February 29, 2012 / Rules and Regulations 12179 

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 January 

26, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–4437 Filed 2–28–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0182; Directorate 

Identifier 2012–CE–005–AD; Amendment 

39–16958; AD 2012–03–52] 

RIN 2120–AA64 

Airworthiness Directives; Mooney 

Aviation Company, Inc. (Mooney) 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Mooney Aviation Company, Inc. 

(Mooney) Models M20R and M20TN 

airplanes. This emergency AD was sent 

previously to all known U.S. owners 

and operators of these airplanes. This 

AD requires inspecting the tail pitch 

trim assembly for correct positioning 

and proper attachment and inspecting 

the Huck Bolt fasteners for proper 

security with repair as necessary. The 

AD also requires sending the inspection 

results to the FAA and Mooney. This 

AD was prompted by a report of an 

incident on a Mooney Model M20TN 

airplane regarding failure of the tail 

pitch trim assembly, which could result 

in loss of control. We are issuing this 

AD to correct the unsafe condition on 

these products. 

DATES: This AD is effective February 29, 

2012 to all persons except those persons 

to whom it was made immediately 

effective by Emergency AD 2012–03–52, 

issued on February 10, 2012, which 

contained the requirements of this 

amendment. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication identified in the 

AD as of February 29, 2012. 

We must receive comments on this 

AD by April 16, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Mooney Aviation 

Company, Inc., 165 Al Mooney Road 

North, Kerrville, Texas 78028; 

telephone: (830) 896–6000; email: 

technicalsupport@mooney.com; 

Internet: www.mooney.com. 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. 

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 this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (phone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Andrew McAnaul, Aerospace Engineer, 

ASW–150 (c/o MIDO–43), 10100 

Reunion Place, Suite 650, San Antonio, 

Texas 78216; telephone: (210) 308– 

3365; facsimile: (210) 308–3370; email: 

andrew.mcanaul@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On February 10, 2012, we issued 

Emergency AD 2012–03–52, which 

requires inspecting the trim fitting, 

hinge, and filler plate of the tail pitch 

trim assembly for correct positioning 

and proper attachment and inspecting 

the Huck Bolt fasteners for proper 

security on certain Mooney Aviation 

Company, Inc. (Mooney) Models M20R 

and M20TN airplanes. If incorrect 

positioning or improper/loose 

attachment is found, the owner/operator 

must contact Mooney for FAA-approved 

repair instructions. The AD also 

requires sending the inspection results 

to the FAA and Mooney. This 

emergency AD was sent previously to 

all known U.S. owners and operators of 

these airplanes. 

This AD action was prompted by a 

report of an incident on a Mooney 

Model M20TN airplane regarding the 

tail pitch trim assembly. In this report, 

the affected airplane experienced an uncommanded significant pitch up 

attitude within seconds after takeoff and 

during the climb. The pilot then pushed 

the yoke forward and the aircraft still 

maintained a nose-up attitude. 

The pilot stated that the ‘‘forces acting 

on the control column were so large that 

single pilot wasn’t able to handle that 

for more than just a few minutes.’’ The 

pilot and copilot had to use their knees 

to hold forward pressure on the flight 

controls to aid in preventing a departure 

from controlled flight. They had to 

maintain between 80 to 100 percent 

power to keep the aircraft at about 90 

knots indicated airspeed to prevent the 

airplane from stalling. The only way 

they were able to descend was to 

introduce a series of turns. 

On Mooney Models M20TN and 

M20R airplanes, the pitch trim is 

adjusted by rotating the entire tail 

assembly. The actuating arm pushes on 

a hinge fixed to the empennage forward 

bulkhead. The hinge attaches to the 

bulkhead using 10 Huck Bolt fasteners 

with swaged collars. 

This aircraft was immediately 

inspected, and all 10 swaged collars that 

hold the tail trim assembly together had 

become unattached. 

Mooney inspected several other 

aircraft and found that on one airplane 

the filler plate was incorrectly installed. 

The filler plate was not correctly 

installed between the aft side of the 

hinge and the bulkhead. Instead, the 

filler plate was located on the forward 

side of the hinge between the hinge and 

trim fitting. It was then noted the 

incident aircraft had the same issue, as 

shown in the upper circle of figure 1. 

Because the hinge has a lip on the 

bottom, on the side toward the bulkhead 

(as shown in the bottom circle of figure 

1), if the filler plate is not installed 

correctly, the hinge will not fit flush 

against the bulkhead, the Huck Bolt 

fasteners will not fit perpendicular to 

the bulkhead, and the collars will not 

swage properly. The condition also 

causes excessive tension pre-load on the 

Huck Bolts. 


tkelley on DSK3SPTVN1PROD with RULES