Federal Register / Vol. 77, No. 139 / Thursday, July 19, 2012 / Rules and Regulations 42419 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0758; Directorate 

Identifier 2012–CE–027–AD; Amendment 

39–17129; AD 2012–14–15] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International, Inc. Global Navigation 

Satellite Sensor Units 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

aircraft equipped with Honeywell 

International, Inc. Model KGS200 

Mercury2 wide area augmentation 

system (WAAS) global navigation 

satellite sensor units (GNSSU). This AD 

requires you cease all localizer 

performance (LP), localizer performance 

with vertical guidance (LPV), and 

satellite based augmentation system 

(SBAS) lateral navigation/vertical 

navigation (LNAV/VNAV) approaches 

until a software problem is corrected. 

This AD was prompted by a report and 

follow-up investigation of a software 

problem that occurred during flight test 

trials of SBAS-capable aircraft using a 

similar Honeywell global positioning 

system (GPS) sensor and the same 

software as the Model KGS200 Mercury2

GNSSU. A software problem occurred 

that could result in misleading 

information during LP, LPV, or SBAS 

LNAV/VNAV approaches. We are 

issuing this AD to correct the unsafe 

condition on these products. 

DATES: This AD is effective July 19, 

2012. 

We must receive comments on this 

AD by September 4, 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: 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. 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 (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

• Non-Pilatus aircraft-related: Albert 

Ma, Aerospace Engineer, Wichita 

Aircraft Certification Office, FAA, 1801 

S. Airport Road, Room 100, Wichita, 

Kansas 67209; phone: (316) 946–4151; 

fax: (316) 946–4107; email: 

albert.ma@faa.gov. 

• Pilatus aircraft-related: Doug 

Rudolph, Aerospace Engineer, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

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

329–4090; email: 

doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report that during flight 

test trials of SBAS-capable aircraft using 

a similar Honeywell GPS sensor with 

the same software as the Honeywell 

International, Inc. Model KGS200 

Mercury2 WAAS GNSSU, a software 

problem occurred that could result in 

misleading information during LP, LPV, 

or SBAS LNAV/VNAV approaches. 

Investigation found the GPS receiver 

could compute an incorrect ionospheric 

correction and error estimate such that 

the error estimate no longer bounds the 

error and the downstream monitor 

cannot detect it. This can potentially 

lead to hazardously misleading 

information. 

The software problem is due to a 

mathematical rounding error, which 

results in misleading information. 

At this time, the only type-certificated 

airplanes that the product is installed in 

is Pilatus PC–12/47E airplanes. 

This condition, if not corrected, could 

result in misleading information during 

instrument meteorological conditions, 

which could prevent the aircraft from 

performing safe instrument approach 

procedures, causing controlled flight 

into terrain. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires incorporating 

airworthiness limitations and placards 

that prohibit LP, LPV, and SBAS LNAV/ 

VNAV approaches until the software 

problem is corrected. 

Interim Action 

We consider this AD interim action. If 

and when new software is developed, 

the FAA will evaluate this software and 

may take further rulemaking action. 

FAA’s Justification and 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 this condition, if not 

corrected, could result in misleading 

information during instrument 

meteorological conditions, which could 

prevent the aircraft from performing safe 

instrument approach procedures, 

causing controlled flight into terrain. 

Therefore, we find that notice and 

opportunity for prior public comment 

are impracticable and that good cause 

exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2012–17129 and Directorate 

Identifier 2012–CE–027–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. 

Costs of Compliance 

We estimate that this AD affects 195 

GNSSU installed on, but not limited to, 


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42420 Federal Register / Vol. 77, No. 139 / Thursday, July 19, 2012 / Rules and Regulations 

PILATUS AIRCRAFT LTD. Model 

PILATUS PC–12/47E airplanes of U.S. 

registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Incorporate language into the limitations section of the flight 

manual and manufacture and install a placard.

0.5 work-hour × $85 per hour 

= $42.50.

$5 $47.50 $9,263 

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 

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), 

(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. 

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 airworthiness 

directive (AD): 

2012–14–15 Honeywell International, Inc.: 

Amendment 39–17129; Docket No. 

FAA–2012–0758; Directorate Identifier 

2012–CE–027–AD. 

(a) Effective Date 

This AD is effective July 19, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to all Honeywell 

International, Inc. Model KGS200 Mercury2

wide area augmentation system (WAAS) 

global navigation satellite sensor units 

(GNSSU), Honeywell part numbers (P/N) 

066–01201–0102 and 066–01201–0104. 

(2) This product is installed on, but not 

limited to, PILATUS AIRCRAFT LTD. Model 

PILATUS PC–12/47E airplanes, certificated 

in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 3457, Navigation. 

(e) Unsafe Condition 

This AD was prompted by a report and 

follow-up investigation of a software problem 

that occurred during flight test trials of 

satellite based augmentation system (SBAS)- 

capable aircraft using a similar Honeywell 

global positioning system (GPS) sensor and 

the same software as the Model KGS200 

Mercury2 GNSSU. A software problem 

occurred that could result in misleading 

information during localizer performance 

(LP), localizer performance with vertical 

guidance (LPV), or SBAS lateral navigation/ 

vertical navigation (LNAV/VNAV) 

approaches. We are issuing this AD to correct 

the unsafe condition on these products. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Incorporate Language Into the 

Limitations Section of the Aircraft Flight 

Manual 

(1) Before further flight after July 19, 2012 

(the effective date of this AD), incorporate 

language into the limitations section of the 

aircraft flight manual (AFM) that states, 

‘‘localizer performance (LP), localizer 

performance with vertical guidance (LPV), 

and satellite based augmentation system 

(SBAS) lateral navigation/vertical navigation 

(LNAV/VNAV) approach operations are 

prohibited.’’ If it can be determined by a 

review of the AFM that the aircraft does not 

have LP capability and uses barometric 

vertical navigation (VNAV), then it is 

permissible to incorporate language into the 

limitation section of the AFM that states, 

‘‘local performance with vertical guidance 

(LPV) approaches are prohibited.’’ 

(2) The AFM action required by this AD 

may be done by an owner/operator (pilot) 

holding at least a private pilot certificate and 

must be entered into the aircraft records 

showing compliance with this AD in 

accordance with 14 CFR 43.9 (a)(1)(4) and 14 

CFR 91.417(a)(2)(v). The record must be 

maintained as required by 14 CFR §§ 91.173, 

121.380, or 135.439. 

(h) Fabricate and Install a Placard 

(1) Within 3 days after July 19, 2012 (the 

effective date of this AD), fabricate and 

install a placard that states, ‘‘LP, LPV, and 

SBAS LNAV/VNAV approaches are 

prohibited.’’ If it can be determined by a 

review of the AFM that the aircraft does not 

have LP capability and uses VNAV, then it 

is permissible to use a placard that states, 

‘‘LPV approaches are prohibited.’’ 

(2) The placard shall be manufactured so 

that the font size is at least an 1⁄8′′ with black 

lettering on a white background. The placard 

must be fabricated and installed by a 

certificated aircraft mechanic on the 

instrument panel in clear view of the pilot. 

(i) Special Flight Permit 

Special flight permits are prohibited for 

this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita Aircraft 

Certification Office (ACO), 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, 


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Federal Register / Vol. 77, No. 139 / Thursday, July 19, 2012 / Rules and Regulations 42421 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

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: 

(1) Non-Pilatus aircraft-related: Albert Ma, 

Aerospace Engineer, Wichita Aircraft 

Certification Office, FAA, 1801 S. Airport 

Road, Room 100, Wichita, Kansas 67209; 

phone: (316) 946–4151; fax: (316) 946–4107; 

email: albert.ma@faa.gov; or 

(2) Pilatus aircraft-related: Doug Rudolph, 

Aerospace Engineer, FAA, Small Airplane 

Directorate, 901 Locust, Room 301, Kansas 

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

4059; fax: (816) 329–4090; email: doug.

rudolph@faa.gov. 

(l) Material Incorporated by Reference 

None. 

Issued in Kansas City, Missouri, on July 13, 

2012. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2012–17592 Filed 7–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0716; Directorate 

Identifier 2012–SW–011–AD; Amendment 

39–17121; AD 2012–14–07] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting an 

airworthiness directive (AD) 

superseding an existing airworthiness 

directive for Bell Helicopter Textron 

Canada (Bell) Model 407 and 427 

helicopters. The existing AD requires 

inspecting certain hydraulic servo 

actuators (servo) to determine whether 

the shaft turns independently of the nut 

or the clevis assembly, and additional 

actions based upon the inspection’s 

outcome. The AD also requires 

reidentifying the servo. Since we issued 

that AD, Bell has learned that additional 

servos may need repair or removal. This 

AD expands the scope of the current AD 

to include inspections for all servos, and 

requires that servos meeting inspection 

requirements be marked with the letter 

‘‘V’’ after the part number on the data 

plate. The actions are intended to detect 

any loose or misaligned parts in the 

servo that could lead to failure of the 

servo and subsequent loss of helicopter 

control. 

DATES: This AD becomes effective 

August 3, 2012. 

We must receive comments on this 

AD by September 17, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. 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 

Operations Office between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the economic 

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. 

For service information identified in 

this AD, contact contact Bell Helicopter 

Textron Canada Limited, 12,800 Rue de 

l’Avenir, Mirabel, Quebec J7J1R4; 

telephone (450) 437–2862 or (800) 363– 

8023; fax (450) 433–0272; or at http://

www.bellcustomer.com/files/. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: Matt 

Wilbanks, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

On September 19, 2011, we issued AD 

2011–15–51, Amendment 39–16817 (76 

FR 66609, October 27, 2011) for Bell 

Model 407 helicopters with a servo, part 

number (P/N) 206–076–062–105 or 206– 

076–062–107, and Bell Model 427 

helicopters, with a servo, P/N 206–076– 

062–109 or 206–076–062–111, installed. 

This AD requires inspecting certain 

servos to determine whether the shaft 

turns independently of the nut or the 

clevis assembly. If the shaft turns 

independently, this AD requires 

replacing the servo with an airworthy 

servo. If the shaft does not turn 

independently, the AD requires 

inspecting to determine the condition of 

the lock washers. Based on the 

condition of the lock washers, the AD 

requires either replacing the servo with 

an airworthy servo or bending the tab of 

the lock washer flush against a flat 

surface of the nut or clevis assembly. 

The AD also requires reidentifying the 

servo by metal-impression stamping or 

vibro-etching ‘‘67–01’’ onto the 

modification plate. The AD was 

prompted by a report that a supplier had 

a ‘‘quality escape’’ resulting in servos 

with a loose nut, shaft, and clevis 

assembly because of improper lockwasher installation. An investigation 

after an accident revealed the clevis nut 

on the servo was loose. Transport 

Canada, which is the aviation authority 

for Canada, notified the FAA of this 


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