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Rules and Regulations Federal Register

66747 

Vol. 70, No. 212 

Thursday, November 3, 2005 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21998; Directorate 

Identifier 2005–CE–40–AD; Amendment 39– 

14358; AD 2005–22–14] 

RIN 2120–AA64 

Airworthiness Directives; GROB– 

WERKE Model G120A Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for all 

GROB–WERKE Model G120A airplanes. 

This AD requires you to inspect for 

signs of any chafing damage to the 

attachment cables of the switch panels 

below the left-hand instrument panel, 

any damaged switch below the switch 

panels of the left-hand instrument 

panel, any damaged (that is, sharp) edge 

of the support tray for the attachment 

cables of the switch panels below the 

left-hand instrument panel; correct any 

damage found during the inspection; 

and apply a layer of anti-rub (protective 

padding) strips to the edge of the 

support tray. This AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

airworthiness authority for Germany. 

We are issuing this AD to detect, 

correct, and prevent chafing of the 

cables against the rear lip of the tray that 

holds the switch panels. Chafing of the 

electrical cables could result in smoke 

or fire in the cockpit. 

DATES: This AD becomes effective on 

December 19, 2005. 

As of December 19, 2005, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: To get the service 

information identified in this AD, 

contact GROB Luft-und Raumfahrt, 

Lettenbachstrasse 9, D–86874 

Tussenhausen-Mattsies, Federal 

Republic of Germany; telephone: 011 49 

8268 998139; facsimile: 011 49 8268 

998200. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590– 

001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2005–21998; Directorate Identifier 

2005–CE–40–AD. 

FOR FURTHER INFORMATION CONTACT: Karl 

Schletzbaum, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4146; facsimile: 

(816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD? 

The Luftfahrt-Bundesamt (LBA), which 

is the airworthiness authority for 

Germany, recently notified FAA that an 

unsafe condition may exist on all GROB 

Model G120A airplanes. The LBA 

reports that GROB received a report of 

smoke in the cockpit on a Model G120A 

airplane. The emergency avionic switch 

on the switch panel below the left-hand 

instrument panel was identified as the 

source of the smoke. 

Chafing of the cables against the rear 

lip of the tray that holds the switch 

panels caused damage of the cable 

insulation. This damage resulted in 

arcing and melting of insulation. 

What is the potential impact if FAA 

took no action? Chafing of the electrical 

cables could result in smoke or fire in 

the cockpit. 

Has FAA taken any action to this 

point? We issued a proposal to amend 

part 39 of the Federal Aviation 

Regulations (14 CFR part 39) to include 

an AD that would apply to all GROB– 

WERKE Model G120A airplanes. This 

proposal was published in the Federal 

Register as a notice of proposed 

rulemaking (NPRM) on August 26, 2005 

(70 FR 50223). The NPRM proposed to 

require you to inspect for signs of any 

chafing damage to the attachment cables 

of the switch panels below the left-hand 

instrument panel, any damaged switch 

below the switch panels of the left-hand 

instrument panel, any damaged (that is, 

sharp) edge of the support tray for the 

attachment cables of the switch panels 

below the left-hand instrument panel; 

correct any damage found during the 

inspection; and apply a layer of anti-rub 

(protective padding) strips to the edge of 

the support tray. 

Comments 

Was the public invited to comment? 

We provided the public the opportunity 

to participate in developing this AD. We 

received no comments on the proposal 

or on the determination of the cost to 

the public. 

Conclusion 

What is FAA’s final determination on 

this issue? We have carefully reviewed 

the available data and determined that 

air safety and the public interest require 

adopting the AD as proposed except for 

minor editorial corrections. We have 

determined that these minor 

corrections: 

—Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

—Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Changes to 14 CFR Part 39—Effect on 

the AD 

How does the revision to 14 CFR part 

39 affect this AD? On July 10, 2002, the 

FAA published a new version of 14 CFR 

part 39 (67 FR 47997, July 22, 2002), 

which governs the FAA’s AD system. 

This regulation now includes material 

that relates to altered products, special 

flight permits, and alternative methods 

of compliance. This material previously 

was included in each individual AD. 

Since this material is included in 14 

CFR part 39, we will not include it in 

future AD actions. 

Costs of Compliance 

How many airplanes does this AD 

impact? We estimate that this AD affects 

6 airplanes in the U.S. registry. 

What is the cost impact of this AD on 

owners/operators of the affected 

airplanes? We estimate the following 

costs to do this inspection, replacement 

of any damaged cable bundle, damaged 

switch, or grinding off any sharp edge 

on the support tray, and installation of 

the protective padding: 

66748 Federal Register / Vol. 70, No. 212 / Thursday, November 3, 2005 / Rules and Regulations 

Labor cost Parts cost Total cost per 

airplane 

Total cost on U.S. 

operators 

1 work hour × $65 an hour = $65 ............................................................................... $20 $85 $85 × 6 = $510. 

Authority for This Rulemaking 

What authority does FAA have for 

issuing this rulemaking action? 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 AD. 

Regulatory Findings 

Will this AD impact various entities? 

We have 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. 

Will this AD involve a significant rule 

or regulatory action? 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 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 summary of the costs 

to comply with this AD (and other 

information as included in the 

Regulatory Evaluation) and placed it in 

the AD Docket. You may get a copy of 

this summary by sending a request to us 

at the address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2005–21998; 

Directorate Identifier 2005–CE–40–AD’’

in your request. 

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 Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. FAA amends § 39.13 by adding a 

new AD to read as follows: 

2005–22–14 GROB–WERKE: Amendment 

39–14358; Docket No. FAA–2005–21998; 

Directorate Identifier 2005–CE–40–AD. 

When Does This AD Become Effective? 

(a) This AD becomes effective on December 

19, 2005. 

What Other ADs Are Affected by This 

Action? 

(b) None. 

What Airplanes Are Affected by This AD? 

(c) This AD affects Model G120A airplanes, 

all serial numbers, that are certificated in any 

category. 

What Is the Unsafe Condition Presented in 

This AD? 

(d) This AD is the result of mandatory 

continuing airworthiness information (MCAI) 

issued by the airworthiness authority for 

Germany. The actions specified in this AD 

are intended to detect, correct, and prevent 

chafing of the cables against the rear lip of 

the tray that holds the switch panels. Chafing 

of the electrical cables could result in smoke 

or fire in the cockpit. 

What Must I Do To Address This Problem? 

(e) To address this problem, you must do 

the following: 

Actions Compliance Procedures 

(1) Inspect for: 

(i) Any signs of chafing damage to the attachment cables of switches below the 

switch panels of the left-hand instrument 

panel; 

Within the next 50 hours time-in-service (TIS) 

after December 19, 2005 (the effective date 

of this AD), unless already done.

Follow GROB Service Bulletin No. MSB1121– 

065, dated July 1, 2005 

(ii) Any damaged switch on switch panels 

of the left-hand instrument panel; and 

(iii) Any damaged (that is, sharp) edge of 

the support tray for the attachment cables of switches below the switch panels 

of the left-hand instrument panel.. 

(2) Correct any damage found as a result of the 

inspection required by paragraph (e)(1) of 

this AD:.

(i) If you find any signs of chafing damage 

to the attachment cables of switches 

below the switch panels of the left-hand 

instrument panel, replace the attachment 

cables; 

(ii) If you find any damaged switch below 

the switch panels of the left-hand instrument panel, replace the switch; and 

Federal Register / Vol. 70, No. 212 / Thursday, November 3, 2005 / Rules and Regulations 66749 

Actions Compliance Procedures 

(iii) If you find any damaged (that is, sharp) 

edge on the support tray for the attachment cables of switches below the 

switch panels of the left-hand instrument 

panel, grind off any sharp edges and 

clean thoroughly. 

Before further flight after the inspection required by paragraph (e)(1) of this AD.Follow GROB Service Bulletin No. MSB1121–

065, dated July 1, 2005. 

(3) Apply anti-rub (padding strips to the edge of 

the support tray for the attachment cables of 

switches below the switch panels of the lefthand instrument panel..

Before further flight after the inspection required by paragraph (e)(1) of this AD. This 

modification is required even if damage is 

not found during the inspections.

Follow GROB Service Bulletin No. MSB1121–

065, dated July 1, 2005. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Standards Office, Small Airplane 

Directorate, FAA. For information on any 

already approved alternative methods of 

compliance, contact Karl Schletzbaum, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

City, Missouri 64106; telephone: (816) 329–

4146; facsimile: (816) 329–4090. 

Is There Other Information That Relates to 

This Subject? 

(g) German AD Number D–2005–242, 

effective date: July 1, 2005, also addresses the 

subject of this AD. 

Does This AD Incorporate Any Material by 

Reference? 

(h) You must do the actions required by 

this AD following the instructions in GROB 

Service Bulletin No. MSB1121–065, dated 

July 1, 2005. The Director of the Federal 

Register approved the incorporation by 

reference of this service bulletin in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. To get a copy of this service 

information, contact GROB Luft-und 

Raumfahrt, Lettenbachstrasse 9, D–86874 

Tussenhausen-Mattsies, Federal Republic of 

Germany; telephone: 011 49 8268 998139; 

facsimile: 011 49 8268 998200. To review 

copies of this service information, go to the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, go 

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

code_of_federal_regulations/ 

ibr_locations.html or call (202) 741–6030. To 

view the AD docket, go to the Docket 

Management Facility; U.S. Department of 

Transportation, 400 Seventh Street, SW., 

Nassif Building, Room PL–401, Washington, 

DC 20590–001 or on the Internet at http:// 

dms.dot.gov. The docket number is FAA–

2005–21998; Directorate Identifier 2005–CE–

40–AD. 

Issued in Kansas City, Missouri, on 

October 25, 2005. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–21800 Filed 11–2–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21835; Directorate 

Identifier 2005–CE–35–AD; Amendment 39–

14357; AD 2005–22–13] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Models PC–12 and PC–12/ 

45 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA adopts a new 

airworthiness directive (AD) for certain 

Pilatus Aircraft Ltd. (Pilatus) Models 

PC–12 and PC–12/45 airplanes. This AD 

requires you to inspect the left and right 

main landing gear (MLG) assemblies for 

any part number (P/N) 532.10.12.077 or 

FAA-approved equivalent part number 

bolts that do not have white primed and 

painted heads; and replace any bolt 

found with new P/N 532.10.12.077F or 

FAA-approved equivalent part number 

bolts in all MLG assemblies. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by the airworthiness authority for 

Switzerland. We are issuing this AD to 

detect and correct any P/N 

532.10.12.077 or FAA-approved 

equivalent part number bolts that do not 

have white primed and painted heads, 

which could result in corrosion of the 

bolt and consequent failure of the bolt. 

This failure could lead to MLG collapse 

during airplane landing and take-off 

operations with consequent loss of 

airplane control. 

DATES: This AD becomes effective on 

December 19, 2005. 

As of December 19, 2005, the Director 

of the Federal Register approved the 

incorporation by reference of certain 

publications listed in the regulation. 

ADDRESSES: To get the service 

information identified in this AD, 

contact Pilatus Aircraft Ltd., Customer 

Liaison Manager, CH–6371 Stans, 

Switzerland; telephone: +41 41 619 

6208; facsimile: +41 41 619 7311; email: SupportPC12@pilatus-aircraft.com 

or from Pilatus Business Aircraft Ltd., 

Product Support Department, 11755 

Airport Way, Broomfield, Colorado 

80021; telephone: (303) 465–9099; 

facsimile: (303) 465–6040. 

To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001 or on the Internet at http:// 

dms.dot.gov. The docket number is 

FAA–2005–21835; Directorate Identifier 

2005–CE–35–AD. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329–

4059; facsimile: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

What events have caused this AD? 

The Federal Office for Civil Aviation 

(FOCA), which is the airworthiness 

authority for Switzerland, recently 

notified FAA that an unsafe condition 

may exist on certain Pilatus Models PC–

12 and PC–12/45 airplanes. The FOCA 

reports part number (P/N) 532.10.12.077 

bolts that do not have white primed and 

painted heads are subject to corrosion. 

These bolts attach the hydraulic 

actuators to the left and right main 

landing gear (MLG) assemblies. The 

FOCA further reports the separation of 

a bolt head in an MLG assembly has 

occurred due to corrosion. The 

corrosion occurred because the bolt 

head was not primed and painted.